**************************************************** * USAF STABILITY AND CONTROL DIGITAL DATCOM * * PROGRAM REV. JAN 96 DIRECT INQUIRIES TO: * * WRIGHT LABORATORY (WL/FIGC) ATTN: W. BLAKE * * WRIGHT PATTERSON AFB, OHIO 45433 * * PHONE (513) 255-6764, FAX (513) 258-4054 * **************************************************** 1 CONERR - INPUT ERROR CHECKING 0 ERROR CODES - N* DENOTES THE NUMBER OF OCCURENCES OF EACH ERROR 0 A - UNKNOWN VARIABLE NAME 0 B - MISSING EQUAL SIGN FOLLOWING VARIABLE NAME 0 C - NON-ARRAY VARIABLE HAS AN ARRAY ELEMENT DESIGNATION - (N) 0 D - NON-ARRAY VARIABLE HAS MULTIPLE VALUES ASSIGNED 0 E - ASSIGNED VALUES EXCEED ARRAY DIMENSION 0 F - SYNTAX ERROR 0****************************** INPUT DATA CARDS ****************************** CASEID APPROXIMATE VISTA F-16D $FLTCON NMACH=1.0,MACH(1)=0.60,NALPHA=11.,ALSCHD(1)=-6.0,-4.0,-2.0,0.0,2.0, ALSCHD(6)=4.0,8.0,12.0,16.0,20.0,24.0,RNNUB(1)=4.28E6$ $OPTINS SREF=8.85,CBARR=2.46,BLREF=4.28$ $SYNTHS XCG=4.14,ZCG=-0.20$ $BODY NX=10.0, X(1)=0.0,0.258,0.589,1.26,2.26,2.59,2.93,3.59,4.57,6.26, S(1)=0.0,0.080,0.160,0.323,0.751,0.883,0.939,1.032,1.032,1.032, P(1)=0.0,1.00,1.42,2.01,3.08,3.34,3.44,3.61,3.61,3.61, R(1)=0.0,.186,.286,.424,.533,.533,.533,.533,.533,.533$ $BODY BNOSE=1.,BLN=2.59,BLA=3.67$ CASEID APPROXIMATE AXISYMMETRIC BODY SOLUTION, EXAMPLE PROBLEM 1, CASE 1 SAVE DUMP CASE NEXT CASE $BODY ZU(1)=-.595,-.476,-.372,-.138,0.200,.334,.343,.343,.343,.343, ZL(1)=-.595,-.715,-.754,-.805,-.868,-.868,-.868,-.868,-.868,-.868$ CASEID ASYMMETRIC (CAMBERED) BODY SOLUTION, EXAMPLE PROBLEM 1, CASE 2 SAVE NEXT CASE $FLTCON NMACH=3.0,MACH(1)=0.90,1.40,2.5,RNNUB(1)=6.4E6,9.96E6,17.8E6$ SAVE CASEID ASYMMETRIC (CAMBERED) BODY SOLUTION, EXAMPLE PROBLEM 1, CASE 3 NEXT CASE $FLTCON NMACH=1.0,MACH(1)=2.5,RNNUB(1)=17.86E6,HYPERS=.TRUE.$ $BODY DS=0.0$ CASEID HYPERSONIC BODY SOLUTION, EXAMPLE PROBLEM 1, CASE 4 NEXT CASE $FLTCON NMACH=4.0,MACH(1)=0.60,0.90,1.40,2.50,LOOP=1.,NALT=4.0, ALT(1)=0.,2000.,40000.,90000.,HYPERS=.FALSE., NALPHA=11.,ALSCHD(1)=-6.0,-4.0,-2.0,0.0,2.0,4.0,8.0,12.0,16.0,20.0,24.0$ $OPTINS SREF=8.85,CBARR=2.46,BLREF=4.28$ $SYNTHS XW=3.61,ZW=-.80,ALIW=2.0,XCG=4.14$ $WGPLNF CHRDTP=0.64,SSPNE=1.59,SSPN=1.59,CHRDR=2.90,SAVSI=55.0,CHSTAT=0.0, TWISTA=0.0,SSPNDD=0.0,DHDADI=0.0,DHDADO=0.0,TYPE=1.0$ $WGSCHR DELTAY=2.85,XOVC=0.40,CLI=0.127,ALPHAI=0.123,CLALPA(1)=.1335, TOVC=0.11,CLMAXL=1.55, CLMAX(1)=1.195,CMO=-.0262,LERI=.0134,CAMBER=.TRUE.,CLAMO=.105,TCEFF=0.055$ CASEID STRAIGHT TAPERED EXPOSED WING SOLUTION, EXAMPLE PROBLEM 2, CASE 1 SAVE DUMP A NEXT CASE $FLTCON NMACH=2.0,MACH(1)=0.60,2.5,LOOP=2.,NALT=2.,ALT(1)=0.,90000.$ $SYNTHS XW=2.497,ZW=-.71$ $WGPLNF SSPNOP=1.11,CHRDBP=2.24,CHRDR=4.01,SAVSI=75.1,SAVSO=55.0,TYPE=3.0$ $WGSCHR TOVC=.10,LERI=0.011,LERO=.0158,TOVCO=0.12,XOVCO=0.40,CMOT=-.0262$ CASEID EXPOSED CRANKED WING SOLUTION, EXAMPLE PROBLEM 2, CASE 2 SAVE NEXT CASE $FLTCON LOOP=3.$ $WGPLNF TYPE=2.0$ CASEID EXPOSED DOUBLE DELTA WING SOLUTION, EXAMPLE PROBLEM 2, CASE 3 NEXT CASE BUILD $FLTCON NMACH=2.0,MACH(1)=.60,.80,NALPHA=9.0,ALSCHD(1)=-2.0,0.0,2.0, 4.0,8.0,12.0,16.0,20.0,24.0,RNNUB(1)=2.28E6,3.04E6$ $FLTCON NMACH=3.0,MACH(1)=0.60,0.80,1.5,RNNUB(1)=4.26E6,6.4E6, 9.96E6,$ $OPTINS SREF=2.25,CBARR=0.822,BLREF=3.00$ $SYNTHS XCG=2.60,ZCG=0.0,XW=1.70,ZW=0.0,ALIW=0.0,XH=3.93, ZH=0.0,ALIH=0.0,XV=3.34,VERTUP=.TRUE.$ $BODY NX=10.0,BNOSE=2.0,BTAIL=1.0,BLN=1.46,BLA=1.97, X(1)=0.0,.175,.322,.530,.850,1.460,2.50,3.43,3.97,4.57, S(1)=0.0,.00547,.0220,.0491,.0872,.136,.136,.136,.0993,.0598, P(1)=0.0,.262,.523,.785,1.04,1.305,1.305,1.305,1.12,.866, R(1)=0.0,.0417,.0833,.125,.1665,.208,.208,.208,.178,.138$ $WGPLNF CHRDTP=0.346,SSPNE=1.29,SSPN=1.50,CHRDR=1.16,SAVSI=45.0,CHSTAT=0.25, TWISTA=0.0,SSPNDD=0.0,DHDADI=0.0,DHDADO=0.0,TYPE=1.0$ $WGSCHR TOVC=.060,DELTAY=1.30,XOVC=0.40,CLI=0.0,ALPHAI=0.0,CLALPA(1)=0.131, CLMAX(1)=.82,CMO=0.0,LERI=.0025,CLAMO=.105,YCM=0.0, SLOPE(1)=70.7,2.7,0.0,-2.5,-3.8,-4.0$ $VTPLNF CHRDTP=.420,SSPNE=.63,SSPN=.849,CHRDR=1.02,SAVSI=28.1, CHSTAT=.25,TWISTA=0.0,TYPE=1.0$ $VTSCHR TOVC=.09,XOVC=0.40,CLALPA(1)=2*0.141,LERI=.0075$ $WGSCHR CLMAXL=0.78$ $HTPLNF CHRDTP=.253,SSPNE=.52,SSPN=.67,CHRDR=.42,SAVSI=45.0,CHSTAT=0.25, TWISTA=0.0,SSPNDD=0.0,DHDADI=0.0,DHDADO=0.0,TYPE=1.0$ $HTSCHR TOVC=0.060,DELTAY=1.30,XOVC=0.40,CLI=0.0,ALPHAI=0.0,CLALPA(1)=.131, CLMAX(1)=0.82,CMO=0.0,LERI=.0025,CLAMO=.105,YCM=0.$ CASEID CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 SAVE NEXT CASE $EXPR01 CLAWB(1)=.0575,CMAWB(1)=-.0050, CDWB(1)=.015,.014,.015,.019,.064,.141,.216,.302,.410, CLWB(1)=-.115,0.0,.115,.23,.47,.65,.76,.81,.90, CMWB(1)=.010,0.0,-.010,-.020,-.038,-.002,-.013,-.013,-.020, CLAB(1)=.002,CMAB(1)=.0039, CDB(1)=.012,.010,.012,.013,.014,.016,.020,.030,.047, CLB(1)=-.004,0.0,.004,.008,.012,.020,.060,.085,.10, CMB(1)=-.0078,.0078,.020,.038,.060,.083,.110,.140,.165,$ $EXPR02 CLAWB(1)=.06,CLAB(1)=.002,CMAB(1)=.0039, ALPOW=0.0,ALPLW=8.8,ACLMW=12.01,CLMW=1.39, ALPOH=0.0,ALPLH=6.2,ACLMH=10.10,CLMH=1.02,$ CASEID INCLUDES BODY AND WING-BODY EXPERIMENTAL DATA, EXAMPLE PROBLEM 3, CASE 2 SAVE NEXT CASE $TVTPAN BVP=0.40,BV=.60,BDV=.36,BH=1.10,SV=.360,VPHITE=20.0,VLP=1.04,ZP=0.0$ CASEID INCLUDES BODY AND WING-BODY EXPERIMENTAL DATA, EXAMPLE PROBLEM 3, CASE 3 SAVE NEXT CASE $FLTCON NMACH=1.0,MACH(1)=.6,RNNUB(1)=2.28E6$ $PROPWR AIETLP=2.0,NENGSP=1.0,THSTCP=0.15,PHALOC=0.0,PHVLOC=0.0,PRPRAD=0.40, ENGFCT=70.0,NOPBPE=4.0,BAPR75=18.0,YP=0.0,CROT=.FALSE.$ CASEID INCLUDES BODY AND WING-BODY EXPERIMENTAL DATA, EXAMPLE PROBLEM 3, CASE 4 SAVE NEXT CASE $FLTCON NMACH=1.0,MACH(1)=.6,RNNUB(1)=2.28E6$ $JETPWR AIETLJ=2.0,NENGSJ=1.0,THSTCJ=.35,JIALOC=0.0,JEVLOC=0.0,JEALOC=0.5, JINLTA=3.0,JEANGL=15.0,JEVELO=4000.,AMBTMP=500.,JESTMP=2000.,JELLOC=0.0, JETOTP=5000.,AMBSTP=500.,JERAD=2.0$ CASEID INCLUDES BODY AND WING-BODY EXPERIMENTAL DATA, EXAMPLE PROBLEM 3, CASE 5 NEXT CASE $FLTCON NMACH=1.0,MACH(1)=0.60,NALPHA=5.,ALSCHD(1)=0.0,5.0,10.0,15.0,20.0, RNNUB(1)=3.1E6$ $OPTINS SREF=694.2,CBARR=18.07,BLREF=45.6$ $SYNTHS XCG=36.68,ZCG=0.0$ $BODY NX=19.0,BNOSE=2.0,BTAIL=2.0,BLN=30.0,BLA=0.0, X(1)=0.0,2.01,5.49,8.975,12.47,15.97,19.47,22.89,26.49,30.0,33.51,37.02, 40.53,44.03,47.53,51.02,54.52,57.99,60.0, S(1)=0.0,2.89,7.42,11.32,14.64,17.36,19.49,21.0,21.91,22.20,21.90, 21.0,19.49,17.36,14.64,12.33,7.42,2.89,0.0, P(1)=0.0,1.84,4.72,7.21,9.32,11.05,12.41,13.36,13.94,14.14,13.94, 13.36,12.41,11.05,9.32,7.21,4.72,1.84,0.0, R(1)=0.0,.293,.752,1.15,1.48,1.76,1.97,2.13,2.22,2.25,2.22,2.13,1.97,1.76, 1.48,1.15,.752,.293,0.0,$ NACA-W-6-65A004 NACA-H-6-65A004 $WGPLNF CHSTAT=0.0, TWISTA=0.0,SSPNDD=0.0,DHDADI=0.0,DHDADO=0.0,TYPE=1.0$ $SYNTHS XW=8.064,ZW=0.0,ALIW=0.0$ $WGPLNF CHRDTP=0.0,SSPNE=6.205,SSPN=8.01,CHRDR=13.87,SAVSI=60.0$ $SYNTHS XH=29.42,ZH=0.0,ALIH=0.0$ $HTPLNF SSPNE=21.34,SSPN=22.82,CHRDR=26.62,SAVSI=38.52,CHSTAT=0.0, CHRDTP=3.80, TWISTA=0.0,SSPNDD=0.0,DHDADI=0.0,DHDADO=0.0,TYPE=1.0,SHB(1)=73.5, SEXT(1)=73.5,RLPH(1)=47.3$ CASEID BODY PLUS WING PLUS CANARD, EXAMPLE PROBLEM 4, CASE 1 NEXT CASE DIM M $FLTCON NMACH=1.0,MACH(1)=2.00,NALPHA=5.,ALSCHD(1)=0.0,5.0,10.0,15.0,20.0, RNNUB(1)=6.56E6,NALT=1.,ALT(1)=27400.$ $OPTINS SREF=64.4933,CBARR=5.5077,BLREF=13.9111$ $SYNTHS XCG=12.1800,ZCG=0.0,SCALE=0.30$ $BODY NX=19.0,BNOSE=2.0,BTAIL=2.0,BLN=9.144,BLA=0.0, X(1)=1.0,1.613,2.673,3.736,4.801,5.868,6.934,8.004,9.074,10.144,11.214, 12.284,13.354,14.420,15.487,16.551,17.618,18.675,19.288, S(1)=0.,.268,.689,1.052,1.360,1.613,1.811,1.951,2.036,2.062,2.085, 1.951,1.811,1.613,1.360,1.053,.689,.268,0., P(1)=0.,.561,1.439,2.198,2.841,3.368,3.783,4.072,4.249,4.310,4.249, 4.072,3.783,3.368,2.841,2.198,1.439,.561,0., R(1)=0.,.089,.229,.351,.451,.536,.600,.649,.677,.686,.677,.649,.600, .536,.451,.351,.229,.089,0.$ NACA-W-S-3-30.0-2.5-20.0 NACA-H-S-1-50.0-2.5 $WGPLNF CHSTAT=0.0, TWISTA=0.0,SSPNDD=0.0,DHDADI=0.0,DHDADO=0.0,TYPE=1.0$ $SYNTHS XW=3.4579,ZW=0.0,ALIW=0.0$ $WGPLNF CHRDTP=0.0,SSPNE=1.8913,SSPN=2.4414,CHRDR=4.2276,SAVSI=60.0$ $SYNTHS XH=9.9672,ZH=0.0,ALIH=0.0$ $HTPLNF SSPNE=6.5044,SSPN=6.9555,CHRDR=8.1138,SAVSI=38.52,CHSTAT=0.0, CHRDTP=1.1582, TWISTA=0.0,SSPNDD=0.0,DHDADI=0.0,DHDADO=0.0,TYPE=1.0,SHB(1)=6.8283, SEXT(1)=6.8284,RLPH(1)=14.4170$ CASEID BODY PLUS WING PLUS CANARD, EXAMPLE PROBLEM 4, CASE 2 NEXT CASE DIM FT PART $FLTCON NALPHA=9.0,ALSCHD(1)=-2.0,0.0,2.0,4.0,8.0, 12.0,16.0,20.0,24.0$ $FLTCON NMACH=1.0,MACH(1)=0.60,RNNUB(1)=4.26E6$ $OPTINS SREF=2.25,CBARR=0.822,BLREF=3.00$ $SYNTHS XCG=2.60,ZCG=0.0,XW=1.70,ZW=0.0,ALIW=0.0$ $BODY NX=10.0,BNOSE=2.0,BTAIL=1.0,BLN=1.46,BLA=1.97, X(1)=0.0,.175,.322,.530,.85,1.46,2.50,3.43,3.97,4.57, R(1)=0.0,.0417,.0833,.125,.1665,.208,.208,.208,.178,.138$ $WGPLNF CHRDTP=0.346,SSPNE=1.29,SSPN=1.50,CHRDR=1.16,SAVSI=45.0,CHSTAT=.25, TWISTA=0.0,SSPNDD=0.0,DHDADI=0.0,DHDADO=0.0,TYPE=1.0$ $WGSCHR TOVC=.060,DELTAY=1.30,XOVC=0.40,CLI=0.0,ALPHAI=0.0,CLALPA(1)=0.131, CLMAX(1)=.82,CM0=0.0,LERI=0.0025,CLAMO=.105,YCM=0.0$ $WGSCHR CLMAXL=.8,TCEFF=.03$ CASEID BODY-WING DAMPING DERIVATIVES, EXAMPLE PROBLEM 5, CASE 1 DAMP SAVE DUMP DYN NEXT CASE $SYMFLP NDELTA=6.0,DELTA(1)=0.,10.,20.,30.,40.,60.,PHETE=.0522,CHRDFI=.2094, CHRDFO=.1554,SPANFI=.208,SPANFO=.708,FTYPE=1.0,CB=.01125,TC=.0225, PHETEP=.0391,NTYPE=1.$ CASEID PLAIN FLAPS ON WING, EXAMPLE PROBLEM 5, CASE 2 DUMP FCM NEXT CASE $FLTCON NALPHA=9.0,ALSCHD=-2.0,0.0,2.0,4.0,8.0, 12.0,16.0,20.0,24.0$ $FLTCON NMACH=1.0,MACH(1)=0.60,RNNUB(1)=4.26E6,$ $OPTINS SREF=2.25,CBARR=0.822,BLREF=3.00$ $SYNTHS XCG=2.60,ZCG=0.0,XW=1.70,ZW=0.0,ALIW=0.0$ $BODY NX=10.0,BNOSE=2.0,BTAIL=1.0,BLN=1.46,BLA=1.97, X(1)=0.0,.175,.322,.530,.85,1.46,2.50,3.43,3.97,4.57, R(1)=0.0,.0417,.0833,.125,.1665,.208,.208,.208,.178,.138$ $WGPLNF CHRDTP=0.346,SSPNE=1.29,SSPN=1.50,CHRDR=1.16,SAVSI=45.0,CHSTAT=.25, TWISTA=0.0,SSPNDD=0.0,DHDADI=0.0,DHDADO=0.0,TYPE=1.0$ $WGSCHR TOVC=.060,DELTAY=1.30,XOVC=0.40,CLI=0.0,ALPHAI=0.0,CLALPA(1)=0.131, CLMAX(1)=.82,CM0=0.0,LERI=0.0025,CLAMO=.105,YCM=0.0$ $ASYFLP DELTAL(1)=5.,10.,20.,30.,40.,DELTAR(1)=-2.,-5.,-10.,-15.,-20., STYPE=4.0, NDELTA=5.,CHRDFI=.1116,CHRDFO=.0692,SPANFI=1.108,SPANFO=1.50,PHETE=.0522$ CASEID PLAIN FLAP AILERON, EXAMPLE PROBLEM 6, CASE 1 SAVE NEXT CASE $ASYFLP STYPE=3.0,DELTAD(1)=.0130,.0261,.0380,.0513,.0630,.0750, DELTAS(1)=.013,.0261,.038,.0513,.063,.075, XSOC(1)=.6980, .6955,.6880,.6638,.6456,.6250,XSPRME=.55,HSOC(1)=.0357,.0710,.0956,.1182, .1365,.1359$ CASEID SPOILER-SLOT-DEFLECTOR ON WING, EXAMPLE PROBLEM 6, CASE 2 NEXT CASE $FLTCON NMACH=1.0,MACH(1)=.60,NALPHA=9.0,ALSCHD(1)=-2.0,0.0,2.0,4.0,8.0, 12.0,16.0,20.0,24.0,RNNUB(1)=2.28E6$ $OPTINS SREF=2.25,CBARR=0.822,BLREF=3.0$ $SYNTHS XCG=2.60,ZCG=0.0,XW=1.70,ZW=0.0,ALIW=0.0,XH=3.93,ZH=0.0,ALIH=0.0, XV=3.34,VERTUP=.TRUE.$ $BODY NX=10., X(1)=0.0,.175,.322,.530,.85,1.46,2.50,3.43,3.97,4.57, R(1)=0.0,.0417,.0833,.125,.1665,.208,.208,.208,.178,.138$ $WGPLNF CHRDTP=0.346,SSPNE=1.29,SSPN=1.50,CHRDR=1.16,SAVSI=45.0,CHSTAT=.25, TWISTA=0.0,SSPNDD=0.0,DHDADI=0.0,DHDADO=0.0,TYPE=1.0$ $WGSCHR TOVC=.060,DELTAY=1.30,XOVC=0.40,CLI=0.0,ALPHAI=0.0,CLALPA(1)=0.131, CLMAX(1)=.82,CM0=0.0,LERI=0.0025,CLAMO=.105,YCM=0.0$ $WGSCHR CLMAXL=0.78$ $VTPLNF CHRDTP=.420,SSPNE=.63,SSPN=.849,CHRDR=1.02,SAVSI=28.1, CHSTAT=.25,TWISTA=0.0,TYPE=1.0$ $VTSCHR TOVC=.09,XOVC=0.40,CLALPA(1)=0.141,LERI=.0075$ $HTPLNF CHRDTP=.253,SSPNE=.52,SSPN=.67,CHRDR=.42,SAVSI=45.0,CHSTAT=0.25, TWISTA=0.0,SSPNDD=0.0,DHDADI=0.0,DHDADO=0.0,TYPE=1.0$ $HTSCHR TOVC=0.060,DELTAY=1.30,XOVC=0.40,CLI=0.0,ALPHAI=0.0,CLALPA(1)=.131, CLMAX(1)=0.82,CMO=0.0,LERI=.0025,CLAMO=.105,YCM=0.0$ $SYMFLP FTYPE=1.0,NDELTA=9.,DELTA(1)=-60.,-40.,-20.,-10.,0.,10., 20.,40.,60.,PHETE=.0522,PHETEP=.0523,SPANFI=.18,SPANFO=.670,CHRDFI=.075, CHRDFO=.051,CB=.0038,TC=.0076,NTYPE=1.0,$ $EXPR01 CLWB(1)=.09,.204,.330,.450,.690,.895,1.070,1.180,1.174$ TRIM CASEID INCLUDES HIGH LIFT EFFECT ON WING, EXAMPLE PROBLEM 7 NEXT CASE $FLTCON NMACH=1.0,MACH(1)=0.60,NALPHA=9.0,ALSCHD(1)=-2.0,0.0,2.0,4.0,8.0, 12.0,16.0,20.0,24.0,RNNUB(1)=2.28E6$ $OPTINS SREF=2.25,CBARR=0.822,BLREF=3.00$ $SYNTHS XCG=2.60,ZCG=0.0,XW=1.70,ZW=0.0,ALIW=0.0,XH=3.93,ZH=0.0,ALIH=0.0, XV=3.34,VERTUP=.TRUE.$ $SYNTHS HINAX=4.271$ $BODY NX=10.0, X(1)=0.0,.175,.322,.530,.85,1.46,2.50,3.43,3.97,4.57, R(1)=0.0,.0417,.0833,.125,.1655,.208,.208,.208,.178,.138$ $WGPLNF CHRDTP=0.346,SSPNE=1.29,SSPN=1.50,CHRDR=1.16,SAVSI=45.0,CHSTAT=.25, TWISTA=0.0,SSPNDD=0.0,DHDADI=0.0,DHDADO=0.0,TYPE=1.0$ $WGSCHR TOVC=.060,DELTAY=1.30,XOVC=0.40,CLI=0.0,ALPHAI=0.0,CLALPA(1)=0.131, CLMAX(1)=.82,CM0=0.0,LERI=0.0025,CLAMO=.105,YCM=0.0$ $WGSCHR CLMAXL=0.78$ $VTPLNF CHRDTP=.420,SSPNE=.63,SSPN=.849,CHRDR=1.02,SAVSI=28.1, CHSTAT=.25,TWISTA=0.0,TYPE=1.0$ $VTSCHR TOVC=.09,XOVC=0.04,CLALPA(1)=0.141,LERI=.0075$ $HTPLNF CHRDTP=.253,SSPNE=.52,SSPN=.67,CHRDR=.42,SAVSI=45.0,CHSTAT=0.25, TWISTA=0.0,SSPNDD=0.0,DHDADI=0.0,DHDADO=0.0,TYPE=1.0$ $HTSCHR TOVC=0.060,DELTAY=1.30,XOVC=0.40,CLI=0.0,ALPHAI=0.0,CLALPA(1)=.131, CLMAX(1)=0.82,CMO=0.0,LERI=.0025,CLAMO=.105,YCM=0.0$ CASEID ALL MOVEABLE HORIZONTAL TAIL, EXAMPLE PROBLEM 8 TRIM NEXT CASE $FLTCON NMACH=1.0,MACH(1)=.26,NALPHA=6.0,ALSCHD(1)=-5.0,0.0,5.0,10.0,15.0, 20.0,RNNUB(1)=1.86E6$ $LARWB ZB=0.0,SREF=.989,DELTEP=90.0,SFRONT=.307,AR=1.076,L=1.915,SWET=2.28, PERBAS=2.38,SBASE=0.307,HB=.595,BB=1.03,BLF=.FALSE.,XCG=1.44,THETAD=15.0, ROUNDN=.FALSE.,SBS=.57,SBSLB=.0228,XCENSB=1.277,XCENW=1.277$ CASEID LIFTING BODY WITH SHARP LEADING EDGE, EXAMPLE PROBLEM 9 NEXT CASE $FLTCON MACH(1)=10.0,NMACH=1.0,RNNUB(1)=1.E7,PINF(1)=10.,HYPERS=.TRUE.$ $TRNJET TIME(1)=1.,2.,3.,4.,5.,FC(1)=1000.,2000.,1000.,500.,200.,NT=5., ALPHA(1)=0.,3.,6.,9.,13.,LAMNRJ(1)=.FALSE.,.FALSE.,.FALSE.,.FALSE., .TRUE.,ME=2.39,ISP=225.,SPAN=2.0,PHE=30.,GP=1.2,CC=90.,LFP=10.$ CASEID TRANSVERSE-JET SIZING, EXAMPLE PROBLEM 10 DUMP JET NEXT CASE $FLTCON NMACH=1.,MACH(1)=10.,NALPHA=5.,ALSCHD(1)=0.,5.,10.,15.,20., RNNUB(1)=1.06E5,HYPERS=.TRUE.$ $OPTINS SREF=1.,CBARR=1.$ $HYPEFF ALITD=150000.,XHL=8.,TWOTI=3.122,CF=2.0,HDELTA(1)=0.,2.,4.,6., 10.,12.,16.,20.,25.,30.,LAMNR=.TRUE.,HNDLTA=10.$ CASEID FLAT PLATE WITH FLAP IN HYPERSONIC FLOW, EXAMPLE PROBLEM 11 NEXT CASE 1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE. 0 CASEID APPROXIMATE VISTA F-16D $FLTCON NMACH=1.0,MACH(1)=0.60,NALPHA=11.,ALSCHD(1)=-6.0,-4.0,-2.0,0.0,2.0, ALSCHD(6)=4.0,8.0,12.0,16.0,20.0,24.0,RNNUB(1)=4.28E6$ $OPTINS SREF=8.85,CBARR=2.46,BLREF=4.28$ $SYNTHS XCG=4.14,ZCG=-0.20$ $BODY NX=10.0, X(1)=0.0,0.258,0.589,1.26,2.26,2.59,2.93,3.59,4.57,6.26, S(1)=0.0,0.080,0.160,0.323,0.751,0.883,0.939,1.032,1.032,1.032, P(1)=0.0,1.00,1.42,2.01,3.08,3.34,3.44,3.61,3.61,3.61, R(1)=0.0,.186,.286,.424,.533,.533,.533,.533,.533,.533$ $BODY BNOSE=1.,BLN=2.59,BLA=3.67$ CASEID APPROXIMATE AXISYMMETRIC BODY SOLUTION, EXAMPLE PROBLEM 1, CASE 1 SAVE DUMP CASE NEXT CASE 0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000 BD( 1)= 6.26000E+00 BD( 2)= 3.59000E+00 BD( 3)= 1.03200E+00 BD( 4)= 1.03200E+00 BD( 5)= 6.26000E+00 BD( 6)= 1.03200E+00 BD( 7)= 5.66530E+00 BD( 8)= 1.00000E-30 BD( 9)= 8.43444E-01 BD( 10)= 2.08059E-02 BD( 11)= 0.00000E+00 BD( 12)= 1.00000E-30 BD( 13)= 1.00000E-30 BD( 14)= 1.00000E-30 BD( 15)= 1.00000E-30 BD( 16)= 1.00000E-30 BD( 17)= 1.00000E-30 BD( 18)= 1.00000E-30 BD( 19)= 1.00000E-30 BD( 20)= 1.00000E-30 BD( 21)= 1.00000E-30 BD( 22)= 1.00000E-30 BD( 23)= 1.00000E-30 BD( 24)= 1.00000E-30 BD( 25)= 1.00000E-30 BD( 26)= 1.00000E-30 BD( 27)= 1.00000E-30 BD( 28)= 1.00000E-30 BD( 29)= 1.00000E-30 BD( 30)= 1.00000E-30 BD( 31)= 1.00000E-30 BD( 32)= 1.00000E-30 BD( 33)= 4.14000E+00 BD( 34)= 1.00000E-30 BD( 35)= 1.00000E-30 BD( 36)= 1.00000E-30 BD( 37)= 1.00000E-30 BD( 38)= 1.00000E-30 BD( 39)= 1.00000E-30 BD( 40)= 1.00000E-30 BD( 41)= 1.00000E-30 BD( 42)= 1.00000E-30 BD( 43)= 1.00000E-30 BD( 44)= 1.00000E-30 BD( 45)= 1.00000E-30 BD( 46)= 1.00000E-30 BD( 47)= 1.00000E-30 BD( 48)= 1.00000E-30 BD( 49)= 1.00000E-30 BD( 50)= 1.00000E-30 BD( 51)= 1.00000E-30 BD( 52)= 1.00000E-30 BD( 53)= 1.00000E-30 BD( 54)= 1.00000E-30 BD( 55)= 4.69500E+05 BD( 56)= 1.03200E+00 BD( 57)= 1.03200E+00 BD( 58)= 1.00000E-30 BD( 59)= 7.12853E-03 BD( 60)= 1.36774E-02 BD( 61)= 2.08059E-02 BD( 62)= 1.00000E-30 BD( 63)= 1.00000E-30 BD( 64)= 1.00000E-30 BD( 65)= 1.00000E-30 BD( 66)= 1.00000E-30 BD( 67)= 1.00000E-30 BD( 68)= 1.00000E-30 BD( 69)= 1.00000E-30 BD( 70)= 1.00000E-30 BD( 71)= 1.00000E-30 BD( 72)= 1.00000E-30 BD( 73)= 1.00000E-30 BD( 74)= 1.00000E-30 BD( 75)= 5.46109E+00 BD( 76)= 6.21916E-01 BD( 77)= 1.00000E-30 BD( 78)= 1.00000E-30 BD( 79)= 1.00000E-30 BD( 80)= 1.00000E-30 BD( 81)= 0.00000E+00 BD( 82)=-2.00000E-01 BD( 83)= 2.00000E-30 BD( 84)= 1.00000E-30 BD( 85)= 1.14629E+00 BD( 86)= 1.14629E+00 BD( 87)= 1.00000E-30 BD( 88)= 0.00000E+00 BD( 89)= 1.00000E-30 BD( 90)= 2.67928E+07 BD( 91)= 3.79712E+07 BD( 92)= 2.48495E-03 BD( 93)= 1.83698E+01 BD( 94)= 1.10000E+01 BD( 95)= 1.00000E-30 BD( 96)= 1.00000E-30 BD( 97)= 1.00000E-30 BD( 98)= 1.00000E-30 BD( 99)= 1.00000E-30 BD(100)= 1.00000E-30 BD(101)= 1.00000E-30 BD(102)= 1.00000E-30 BD(103)= 1.00000E-30 BD(104)= 1.00000E-30 BD(105)= 1.00000E-30 BD(106)= 1.00000E-30 BD(107)= 1.00000E-30 BD(108)= 1.00000E-30 BD(109)= 1.00000E-30 BD(110)= 1.00000E-30 BD(111)= 1.00000E-30 BD(112)= 1.00000E-30 BD(113)= 1.00000E-30 BD(114)= 1.00000E-30 BD(115)= 1.00000E-30 BD(116)= 1.00000E-30 BD(117)= 1.00000E-30 BD(118)= 1.00000E-30 BD(119)= 1.00000E-30 BD(120)= 1.00000E-30 BD(121)= 1.00000E-30 BD(122)= 1.00000E-30 BD(123)= 1.00000E-30 BD(124)= 1.00000E-30 BD(125)= 1.00000E-30 BD(126)= 1.00000E-30 BD(127)= 1.00000E-30 BD(128)= 1.00000E-30 BD(129)= 1.00000E-30 BD(130)= 1.00000E-30 BD(131)= 1.00000E-30 BD(132)= 1.00000E-30 BD(133)= 1.00000E-30 BD(134)= 1.00000E-30 BD(135)= 1.20000E+00 BD(136)= 1.20000E+00 BD(137)= 1.20000E+00 BD(138)= 1.20000E+00 BD(139)= 1.20000E+00 BD(140)= 1.20000E+00 BD(141)= 1.20000E+00 BD(142)= 1.20000E+00 BD(143)= 1.20000E+00 BD(144)= 1.20052E+00 BD(145)= 1.20440E+00 BD(146)= 1.00000E-30 BD(147)= 1.00000E-30 BD(148)= 1.00000E-30 BD(149)= 1.00000E-30 BD(150)= 1.00000E-30 BD(151)= 1.00000E-30 BD(152)= 1.00000E-30 BD(153)= 1.00000E-30 BD(154)= 1.00000E-30 BD(155)=-2.05992E-02 BD(156)=-1.37328E-02 BD(157)=-6.86641E-03 BD(158)= 0.00000E+00 BD(159)= 6.86641E-03 BD(160)= 1.37328E-02 BD(161)= 2.74656E-02 BD(162)= 4.11985E-02 BD(163)= 5.49313E-02 BD(164)= 6.86641E-02 BD(165)= 8.23969E-02 BD(166)= 1.00000E-30 BD(167)= 1.00000E-30 BD(168)= 1.00000E-30 BD(169)= 1.00000E-30 BD(170)= 1.00000E-30 BD(171)= 1.00000E-30 BD(172)= 1.00000E-30 BD(173)= 1.00000E-30 BD(174)= 1.00000E-30 BD(175)= 1.00000E-30 BD(176)= 1.00000E-30 BD(177)= 1.00000E-30 BD(178)= 1.00000E-30 BD(179)= 1.00000E-30 BD(180)= 1.00000E-30 BD(181)= 1.00000E-30 BD(182)= 1.00000E-30 BD(183)= 1.00000E-30 BD(184)= 1.00000E-30 BD(185)= 1.00000E-30 BD(186)= 1.00000E-30 BD(187)= 1.00000E-30 BD(188)= 1.00000E-30 BD(189)= 1.00000E-30 BD(190)= 1.00000E-30 BD(191)= 1.00000E-30 BD(192)= 1.00000E-30 BD(193)= 1.00000E-30 BD(194)= 1.00000E-30 BD(195)= 0.00000E+00 BD(196)= 0.00000E+00 BD(197)= 0.00000E+00 BD(198)= 0.00000E+00 BD(199)= 0.00000E+00 BD(200)= 0.00000E+00 BD(201)= 0.00000E+00 BD(202)= 0.00000E+00 BD(203)= 0.00000E+00 BD(204)= 0.00000E+00 BD(205)= 0.00000E+00 BD(206)= 1.00000E-30 BD(207)= 1.00000E-30 BD(208)= 1.00000E-30 BD(209)= 1.00000E-30 BD(210)= 1.00000E-30 BD(211)= 1.00000E-30 BD(212)= 1.00000E-30 BD(213)= 1.00000E-30 BD(214)= 1.00000E-30 BD(215)= 2.15321E-03 BD(216)= 9.57953E-04 BD(217)= 2.39634E-04 BD(218)= 0.00000E+00 BD(219)= 2.39634E-04 BD(220)= 9.57953E-04 BD(221)= 3.82248E-03 BD(222)= 8.56564E-03 BD(223)= 1.51411E-02 BD(224)= 2.34845E-02 BD(225)= 3.35139E-02 BD(226)= 1.00000E-30 BD(227)= 1.00000E-30 BD(228)= 1.00000E-30 BD(229)= 1.00000E-30 BD(230)= 1.00000E-30 BD(231)= 1.00000E-30 BD(232)= 1.00000E-30 BD(233)= 1.00000E-30 BD(234)= 1.00000E-30 BD(235)= 1.00000E-30 BD(236)= 1.00000E-30 BD(237)= 1.00000E-30 BD(238)= 1.00000E-30 BD(239)= 1.00000E-30 BD(240)= 1.00000E-30 BD(241)= 1.00000E-30 BD(242)= 1.00000E-30 BD(243)= 1.00000E-30 BD(244)= 1.00000E-30 BD(245)= 1.00000E-30 BD(246)= 1.00000E-30 BD(247)= 1.00000E-30 BD(248)= 1.00000E-30 BD(249)= 1.00000E-30 BD(250)= 1.00000E-30 BD(251)= 1.00000E-30 BD(252)= 1.00000E-30 BD(253)= 1.00000E-30 BD(254)= 1.00000E-30 BD(255)=-6.00000E+00 BD(256)=-4.00000E+00 BD(257)=-2.00000E+00 BD(258)= 0.00000E+00 BD(259)= 2.00000E+00 BD(260)= 4.00000E+00 BD(261)= 8.00000E+00 BD(262)= 1.20000E+01 BD(263)= 1.60000E+01 BD(264)= 2.00000E+01 BD(265)= 2.40000E+01 BD(266)= 1.00000E-30 BD(267)= 1.00000E-30 BD(268)= 1.00000E-30 BD(269)= 1.00000E-30 BD(270)= 1.00000E-30 BD(271)= 1.00000E-30 BD(272)= 1.00000E-30 BD(273)= 1.00000E-30 BD(274)= 1.00000E-30 BD(275)= 1.00000E-30 BD(276)= 1.00000E-30 BD(277)= 1.00000E-30 BD(278)= 1.00000E-30 BD(279)= 1.00000E-30 BD(280)= 1.00000E-30 BD(281)= 1.00000E-30 BD(282)= 1.00000E-30 BD(283)= 1.00000E-30 BD(284)= 1.00000E-30 BD(285)= 1.00000E-30 BD(286)= 1.00000E-30 BD(287)= 1.00000E-30 BD(288)= 1.00000E-30 BD(289)= 1.00000E-30 BD(290)= 1.00000E-30 BD(291)= 1.00000E-30 BD(292)= 1.00000E-30 BD(293)= 1.00000E-30 BD(294)= 1.00000E-30 BD(295)= 1.00000E-30 BD(296)= 1.00000E-30 BD(297)= 1.00000E-30 BD(298)= 1.00000E-30 BD(299)= 1.00000E-30 BD(300)= 1.00000E-30 BD(301)= 1.00000E-30 BD(302)= 1.00000E-30 BD(303)= 1.00000E-30 BD(304)= 1.00000E-30 BD(305)= 1.00000E-30 BD(306)= 1.00000E-30 BD(307)= 1.00000E-30 BD(308)= 1.00000E-30 BD(309)= 1.00000E-30 BD(310)= 1.00000E-30 BD(311)= 1.00000E-30 BD(312)= 1.00000E-30 BD(313)= 1.00000E-30 BD(314)= 1.00000E-30 BD(315)= 1.00000E-30 BD(316)= 1.00000E-30 BD(317)= 1.00000E-30 BD(318)= 1.00000E-30 BD(319)= 1.00000E-30 BD(320)= 1.00000E-30 BD(321)= 1.00000E-30 BD(322)= 1.00000E-30 BD(323)= 1.00000E-30 BD(324)= 1.00000E-30 BD(325)= 1.00000E-30 BD(326)= 1.00000E-30 BD(327)= 1.00000E-30 BD(328)= 1.00000E-30 BD(329)= 1.00000E-30 BD(330)= 1.00000E-30 BD(331)= 1.00000E-30 BD(332)= 1.00000E-30 BD(333)= 1.00000E-30 BD(334)= 1.00000E-30 BD(335)= 1.00000E-30 BD(336)= 1.00000E-30 BD(337)= 1.00000E-30 BD(338)= 1.00000E-30 BD(339)= 1.00000E-30 BD(340)= 1.00000E-30 BD(341)= 1.00000E-30 BD(342)= 1.00000E-30 BD(343)= 1.00000E-30 BD(344)= 1.00000E-30 BD(345)= 1.00000E-30 BD(346)= 1.00000E-30 BD(347)= 1.00000E-30 BD(348)= 1.00000E-30 BD(349)= 1.00000E-30 BD(350)= 1.00000E-30 BD(351)= 1.00000E-30 BD(352)= 1.00000E-30 BD(353)= 1.00000E-30 BD(354)= 1.00000E-30 BD(355)= 1.00000E-30 BD(356)= 1.00000E-30 BD(357)= 1.00000E-30 BD(358)= 1.00000E-30 BD(359)= 1.00000E-30 BD(360)= 1.00000E-30 BD(361)= 1.00000E-30 BD(362)= 1.00000E-30 BD(363)= 1.00000E-30 BD(364)= 1.00000E-30 BD(365)= 1.00000E-30 BD(366)= 1.00000E-30 BD(367)= 1.00000E-30 BD(368)= 1.00000E-30 BD(369)= 1.00000E-30 BD(370)= 1.00000E-30 BD(371)= 1.00000E-30 BD(372)= 1.00000E-30 BD(373)= 1.00000E-30 BD(374)= 1.00000E-30 BD(375)= 1.00000E-30 BD(376)= 1.00000E-30 BD(377)= 1.00000E-30 BD(378)= 1.00000E-30 BD(379)= 1.00000E-30 BD(380)= 1.00000E-30 BD(381)= 1.00000E-30 BD(382)= 1.00000E-30 BD(383)= 1.00000E-30 BD(384)= 1.00000E-30 BD(385)= 1.00000E-30 BD(386)= 1.00000E-30 BD(387)= 1.00000E-30 BD(388)= 1.00000E-30 BD(389)= 1.00000E-30 BD(390)= 1.00000E-30 BD(391)= 1.00000E-30 BD(392)= 1.00000E-30 BD(393)= 1.00000E-30 BD(394)= 1.00000E-30 BD(395)= 1.00000E-30 BD(396)= 1.00000E-30 BD(397)= 1.00000E-30 BD(398)= 1.00000E-30 BD(399)= 1.00000E-30 BD(400)= 1.00000E-30 BD(401)= 1.00000E-30 BD(402)= 1.00000E-30 BD(403)= 1.00000E-30 BD(404)= 1.00000E-30 BD(405)= 1.00000E-30 BD(406)= 1.00000E-30 BD(407)= 1.00000E-30 BD(408)= 1.00000E-30 BD(409)= 1.00000E-30 BD(410)= 1.00000E-30 BD(411)= 1.00000E-30 BD(412)= 1.00000E-30 BD(413)= 1.00000E-30 BD(414)= 1.00000E-30 BD(415)= 1.00000E-30 BD(416)= 1.00000E-30 BD(417)= 1.00000E-30 BD(418)= 1.00000E-30 BD(419)= 1.00000E-30 BD(420)= 1.00000E-30 BD(421)= 1.00000E-30 BD(422)= 1.00000E-30 BD(423)= 1.00000E-30 BD(424)= 1.00000E-30 BD(425)= 1.00000E-30 BD(426)= 1.00000E-30 BD(427)= 1.00000E-30 BD(428)= 1.00000E-30 BD(429)= 1.00000E-30 BD(430)= 1.00000E-30 BD(431)= 1.00000E-30 BD(432)= 1.00000E-30 BD(433)= 1.00000E-30 BD(434)= 1.00000E-30 BD(435)= 1.00000E-30 BD(436)= 1.00000E-30 BD(437)= 1.00000E-30 BD(438)= 1.00000E-30 BD(439)= 1.00000E-30 BD(440)= 1.00000E-30 BD(441)= 1.00000E-30 BD(442)= 1.00000E-30 BD(443)= 1.00000E-30 BD(444)= 1.00000E-30 BD(445)= 1.00000E-30 BD(446)= 1.00000E-30 BD(447)= 1.00000E-30 BD(448)= 1.00000E-30 BD(449)= 1.00000E-30 BD(450)= 1.00000E-30 BD(451)= 1.00000E-30 BD(452)= 1.00000E-30 BD(453)= 1.00000E-30 BD(454)= 1.00000E-30 BD(455)= 1.00000E-30 BD(456)= 1.00000E-30 BD(457)= 1.00000E-30 BD(458)= 1.00000E-30 BD(459)= 1.00000E-30 BD(460)= 1.00000E-30 BD(461)= 1.00000E-30 BD(462)= 1.00000E-30 BD(463)= 1.00000E-30 BD(464)= 1.00000E-30 BD(465)= 1.00000E-30 BD(466)= 1.00000E-30 BD(467)= 1.00000E-30 BD(468)= 1.00000E-30 BD(469)= 1.00000E-30 BD(470)= 1.00000E-30 BD(471)= 1.00000E-30 BD(472)= 1.00000E-30 BD(473)= 1.00000E-30 BD(474)= 1.00000E-30 BD(475)= 1.00000E-30 BD(476)= 1.00000E-30 BD(477)= 1.00000E-30 BD(478)= 1.00000E-30 BD(479)= 1.00000E-30 BD(480)= 1.00000E-30 BD(481)= 1.00000E-30 BD(482)= 1.00000E-30 BD(483)= 1.00000E-30 BD(484)= 1.00000E-30 BD(485)= 1.00000E-30 BD(486)= 1.00000E-30 BD(487)= 1.00000E-30 BD(488)= 1.00000E-30 BD(489)= 1.00000E-30 BD(490)= 1.00000E-30 BD(491)= 1.00000E-30 BD(492)= 1.00000E-30 BD(493)= 1.00000E-30 BD(494)= 1.00000E-30 BD(495)= 1.00000E-30 BD(496)= 1.00000E-30 BD(497)= 1.00000E-30 BD(498)= 1.00000E-30 BD(499)= 1.00000E-30 BD(500)= 1.00000E-30 BD(501)= 1.00000E-30 BD(502)= 1.00000E-30 BD(503)= 1.00000E-30 BD(504)= 1.00000E-30 BD(505)= 1.00000E-30 BD(506)= 1.00000E-30 BD(507)= 1.00000E-30 BD(508)= 1.00000E-30 BD(509)= 1.00000E-30 BD(510)= 1.00000E-30 BD(511)= 1.00000E-30 BD(512)= 1.00000E-30 BD(513)= 1.00000E-30 BD(514)= 1.00000E-30 BD(515)= 1.00000E-30 BD(516)= 1.00000E-30 BD(517)= 1.00000E-30 BD(518)= 1.00000E-30 BD(519)= 1.00000E-30 BD(520)= 1.00000E-30 BD(521)= 1.00000E-30 BD(522)= 1.00000E-30 BD(523)= 1.00000E-30 BD(524)= 1.00000E-30 BD(525)= 1.00000E-30 BD(526)= 1.00000E-30 BD(527)= 1.00000E-30 BD(528)= 1.00000E-30 BD(529)= 1.00000E-30 BD(530)= 1.00000E-30 BD(531)= 1.00000E-30 BD(532)= 1.00000E-30 BD(533)= 1.00000E-30 BD(534)= 1.00000E-30 BD(535)= 1.00000E-30 BD(536)= 1.00000E-30 BD(537)= 1.00000E-30 BD(538)= 1.00000E-30 BD(539)= 1.00000E-30 BD(540)= 1.00000E-30 BD(541)= 1.00000E-30 BD(542)= 1.00000E-30 BD(543)= 1.00000E-30 BD(544)= 1.00000E-30 BD(545)= 1.00000E-30 BD(546)= 1.00000E-30 BD(547)= 1.00000E-30 BD(548)= 1.00000E-30 BD(549)= 1.00000E-30 BD(550)= 1.00000E-30 BD(551)= 1.00000E-30 BD(552)= 1.00000E-30 BD(553)= 1.00000E-30 BD(554)= 1.00000E-30 BD(555)= 1.00000E-30 BD(556)= 1.00000E-30 BD(557)= 1.00000E-30 BD(558)= 1.00000E-30 BD(559)= 1.00000E-30 BD(560)= 1.00000E-30 BD(561)= 1.00000E-30 BD(562)= 1.00000E-30 BD(563)= 1.00000E-30 BD(564)= 1.00000E-30 BD(565)= 1.00000E-30 BD(566)= 1.00000E-30 BD(567)= 1.00000E-30 BD(568)= 1.00000E-30 BD(569)= 1.00000E-30 BD(570)= 1.00000E-30 BD(571)= 1.00000E-30 BD(572)= 1.00000E-30 BD(573)= 1.00000E-30 BD(574)= 1.00000E-30 BD(575)= 1.00000E-30 BD(576)= 1.00000E-30 BD(577)= 1.00000E-30 BD(578)= 1.00000E-30 BD(579)= 1.00000E-30 BD(580)= 1.00000E-30 BD(581)= 1.00000E-30 BD(582)= 1.00000E-30 BD(583)= 1.00000E-30 BD(584)= 1.00000E-30 BD(585)= 1.00000E-30 BD(586)= 1.00000E-30 BD(587)= 1.00000E-30 BD(588)= 1.00000E-30 BD(589)= 1.00000E-30 BD(590)= 1.00000E-30 BD(591)= 1.00000E-30 BD(592)= 1.00000E-30 BD(593)= 1.00000E-30 BD(594)= 1.00000E-30 BD(595)= 1.00000E-30 BD(596)= 1.00000E-30 BD(597)= 1.00000E-30 BD(598)= 1.00000E-30 BD(599)= 1.00000E-30 BD(600)= 1.00000E-30 BD(601)= 1.00000E-30 BD(602)= 1.00000E-30 BD(603)= 1.00000E-30 BD(604)= 1.00000E-30 BD(605)= 1.00000E-30 BD(606)= 1.00000E-30 BD(607)= 1.00000E-30 BD(608)= 1.00000E-30 BD(609)= 1.00000E-30 BD(610)= 1.00000E-30 BD(611)= 1.00000E-30 BD(612)= 1.00000E-30 BD(613)= 1.00000E-30 BD(614)= 1.00000E-30 BD(615)= 1.00000E-30 BD(616)= 1.00000E-30 BD(617)= 1.00000E-30 BD(618)= 1.00000E-30 BD(619)= 1.00000E-30 BD(620)= 1.00000E-30 BD(621)= 1.00000E-30 BD(622)= 1.00000E-30 BD(623)= 1.00000E-30 BD(624)= 1.00000E-30 BD(625)= 1.00000E-30 BD(626)= 1.00000E-30 BD(627)= 1.00000E-30 BD(628)= 1.00000E-30 BD(629)= 1.00000E-30 BD(630)= 1.00000E-30 BD(631)= 1.00000E-30 BD(632)= 1.00000E-30 BD(633)= 1.00000E-30 BD(634)= 1.00000E-30 BD(635)= 1.00000E-30 BD(636)= 1.00000E-30 BD(637)= 1.00000E-30 BD(638)= 1.00000E-30 BD(639)= 1.00000E-30 BD(640)= 1.00000E-30 BD(641)= 1.00000E-30 BD(642)= 1.00000E-30 BD(643)= 1.00000E-30 BD(644)= 1.00000E-30 BD(645)= 1.00000E-30 BD(646)= 1.00000E-30 BD(647)= 1.00000E-30 BD(648)= 1.00000E-30 BD(649)= 1.00000E-30 BD(650)= 1.00000E-30 BD(651)= 1.00000E-30 BD(652)= 1.00000E-30 BD(653)= 1.00000E-30 BD(654)= 1.00000E-30 BD(655)= 1.00000E-30 BD(656)= 1.00000E-30 BD(657)= 1.00000E-30 BD(658)= 1.00000E-30 BD(659)= 1.00000E-30 BD(660)= 1.00000E-30 BD(661)= 1.00000E-30 BD(662)= 1.00000E-30 BD(663)= 1.00000E-30 BD(664)= 1.00000E-30 BD(665)= 1.00000E-30 BD(666)= 1.00000E-30 BD(667)= 1.00000E-30 BD(668)= 1.00000E-30 BD(669)= 1.00000E-30 BD(670)= 1.00000E-30 BD(671)= 1.00000E-30 BD(672)= 1.00000E-30 BD(673)= 1.00000E-30 BD(674)= 1.00000E-30 BD(675)= 1.00000E-30 BD(676)= 1.00000E-30 BD(677)= 1.00000E-30 BD(678)= 1.00000E-30 BD(679)= 1.00000E-30 BD(680)= 1.00000E-30 BD(681)= 1.00000E-30 BD(682)= 1.00000E-30 BD(683)= 1.00000E-30 BD(684)= 1.00000E-30 BD(685)= 1.00000E-30 BD(686)= 1.00000E-30 BD(687)= 1.00000E-30 BD(688)= 1.00000E-30 BD(689)= 1.00000E-30 BD(690)= 1.00000E-30 BD(691)= 1.00000E-30 BD(692)= 1.00000E-30 BD(693)= 1.00000E-30 BD(694)= 1.00000E-30 BD(695)= 1.00000E-30 BD(696)= 1.00000E-30 BD(697)= 1.00000E-30 BD(698)= 1.00000E-30 BD(699)= 1.00000E-30 BD(700)= 1.00000E-30 BD(701)= 1.00000E-30 BD(702)= 1.00000E-30 BD(703)= 1.00000E-30 BD(704)= 1.00000E-30 BD(705)= 1.00000E-30 BD(706)= 1.00000E-30 BD(707)= 1.00000E-30 BD(708)= 1.00000E-30 BD(709)= 1.00000E-30 BD(710)= 1.00000E-30 BD(711)= 1.00000E-30 BD(712)= 1.00000E-30 BD(713)= 1.00000E-30 BD(714)= 1.00000E-30 BD(715)= 1.00000E-30 BD(716)= 1.00000E-30 BD(717)= 1.00000E-30 BD(718)= 1.00000E-30 BD(719)= 1.00000E-30 BD(720)= 1.00000E-30 BD(721)= 1.00000E-30 BD(722)= 1.00000E-30 BD(723)= 1.00000E-30 BD(724)= 1.00000E-30 BD(725)= 1.00000E-30 BD(726)= 1.00000E-30 BD(727)= 1.00000E-30 BD(728)= 1.00000E-30 BD(729)= 1.00000E-30 BD(730)= 1.00000E-30 BD(731)= 1.00000E-30 BD(732)= 1.00000E-30 BD(733)= 1.00000E-30 BD(734)= 1.00000E-30 BD(735)= 1.00000E-30 BD(736)= 1.00000E-30 BD(737)= 1.00000E-30 BD(738)= 1.00000E-30 BD(739)= 1.00000E-30 BD(740)= 1.00000E-30 BD(741)= 1.00000E-30 BD(742)= 1.00000E-30 BD(743)= 1.00000E-30 BD(744)= 1.00000E-30 BD(745)= 1.00000E-30 BD(746)= 1.00000E-30 BD(747)= 1.00000E-30 BD(748)= 1.00000E-30 BD(749)= 1.00000E-30 BD(750)= 1.00000E-30 BD(751)= 1.00000E-30 BD(752)= 1.00000E-30 BD(753)= 1.00000E-30 BD(754)= 1.00000E-30 BD(755)= 1.00000E-30 BD(756)= 1.00000E-30 BD(757)= 1.00000E-30 BD(758)= 1.00000E-30 BD(759)= 1.00000E-30 BD(760)= 1.00000E-30 BD(761)= 1.00000E-30 BD(762)= 1.00000E-30 STB( 1)= 1.00000E-30 STB( 2)= 0.00000E+00 STB( 3)= 1.00000E+00 STB( 4)= 1.00000E-30 STB( 5)= 1.00000E-30 STB( 6)= 1.00000E-30 STB( 7)= 1.00000E-30 STB( 8)= 1.00000E-30 STB( 9)= 1.00000E-30 STB( 10)= 1.00000E-30 STB( 11)= 1.00000E-30 STB( 12)= 1.00000E-30 STB( 13)= 1.00000E-30 STB( 14)= 1.00000E-30 STB( 15)= 1.00000E-30 STB( 16)= 1.00000E-30 STB( 17)= 1.00000E-30 STB( 18)= 1.00000E-30 STB( 19)= 1.00000E-30 STB( 20)= 1.00000E-30 STB( 21)= 1.00000E-30 STB( 22)= 1.00000E-30 STB( 23)= 1.00000E-30 STB( 24)= 1.00000E-30 STB( 25)= 1.00000E-30 STB( 26)= 1.00000E-30 STB( 27)= 1.00000E-30 STB( 28)= 1.00000E-30 STB( 29)= 1.00000E-30 STB( 30)= 1.00000E-30 STB( 31)= 1.00000E-30 STB( 32)= 1.00000E-30 STB( 33)= 1.00000E-30 STB( 34)= 1.00000E-30 STB( 35)= 1.00000E-30 STB( 36)= 1.00000E-30 STB( 37)= 1.00000E-30 STB( 38)= 1.00000E-30 STB( 39)= 1.00000E-30 STB( 40)= 1.00000E-30 STB( 41)= 1.00000E-30 STB( 42)= 1.00000E-30 STB( 43)= 1.00000E-30 STB( 44)= 1.00000E-30 STB( 45)= 1.00000E-30 STB( 46)= 1.00000E-30 STB( 47)= 1.00000E-30 STB( 48)= 1.00000E-30 STB( 49)= 1.00000E-30 STB( 50)= 1.00000E-30 STB( 51)= 1.00000E-30 STB( 52)= 1.00000E-30 STB( 53)= 1.00000E-30 STB( 54)= 1.00000E-30 STB( 55)= 1.00000E-30 STB( 56)= 1.00000E-30 STB( 57)= 1.00000E-30 STB( 58)= 1.00000E-30 STB( 59)= 1.00000E-30 STB( 60)= 1.00000E-30 STB( 61)= 1.00000E-30 STB( 62)= 1.00000E-30 STB( 63)= 1.00000E-30 STB( 64)= 1.00000E-30 STB( 65)= 1.00000E-30 STB( 66)= 1.00000E-30 STB( 67)= 1.00000E-30 STB( 68)= 1.00000E-30 STB( 69)= 1.00000E-30 STB( 70)= 1.00000E-30 STB( 71)= 1.00000E-30 STB( 72)= 1.00000E-30 STB( 73)= 1.00000E-30 STB( 74)= 1.00000E-30 STB( 75)= 1.00000E-30 STB( 76)= 1.00000E-30 STB( 77)= 1.00000E-30 STB( 78)= 1.00000E-30 STB( 79)= 1.00000E-30 STB( 80)= 1.00000E-30 STB( 81)= 1.00000E-30 STB( 82)= 1.00000E-30 STB( 83)= 1.00000E-30 STB( 84)= 1.00000E-30 STB( 85)= 1.00000E-30 STB( 86)= 1.00000E-30 STB( 87)= 1.00000E-30 STB( 88)= 1.00000E-30 STB( 89)= 1.00000E-30 STB( 90)= 1.00000E-30 STB( 91)= 1.00000E-30 STB( 92)= 1.00000E-30 STB( 93)= 1.00000E-30 STB( 94)= 1.00000E-30 STB( 95)= 1.00000E-30 STB( 96)= 1.00000E-30 STB( 97)= 1.00000E-30 STB( 98)= 1.00000E-30 STB( 99)= 1.00000E-30 STB(100)= 1.00000E-30 STB(101)= 1.00000E-30 STB(102)= 1.00000E-30 STB(103)= 1.00000E-30 STB(104)= 1.00000E-30 STB(105)= 1.00000E-30 STB(106)= 1.00000E-30 STB(107)= 1.00000E-30 STB(108)= 1.00000E-30 STB(109)= 1.00000E-30 STB(110)= 1.00000E-30 STB(111)= 1.00000E-30 STB(112)= 1.00000E-30 STB(113)= 1.00000E-30 STB(114)= 1.00000E-30 STB(115)= 1.00000E-30 STB(116)= 1.00000E-30 STB(117)= 1.00000E-30 STB(118)= 1.00000E-30 STB(119)= 1.00000E-30 STB(120)= 1.00000E-30 STB(121)= 1.00000E-30 STB(122)= 1.00000E-30 STB(123)= 1.00000E-30 STB(124)= 1.00000E-30 STB(125)= 1.00000E-30 STB(126)= 1.00000E-30 STB(127)= 1.00000E-30 STB(128)= 1.00000E-30 STB(129)= 1.00000E-30 STB(130)= 1.00000E-30 STB(131)= 1.00000E-30 STB(132)= 1.00000E-30 STB(133)= 1.00000E-30 STB(134)= 1.00000E-30 STB(135)= 1.00000E-30 0**** FOLLOWING ARE THE BASIC INPUT DATA BLOCKS **** FLC( 1)= 1.00000E+00 FLC( 2)= 1.10000E+01 FLC( 3)= 6.00000E-01 FLC( 4)= 1.00000E-30 FLC( 5)= 1.00000E-30 FLC( 6)= 1.00000E-30 FLC( 7)= 1.00000E-30 FLC( 8)= 1.00000E-30 FLC( 9)= 1.00000E-30 FLC( 10)= 1.00000E-30 FLC( 11)= 1.00000E-30 FLC( 12)= 1.00000E-30 FLC( 13)= 1.00000E-30 FLC( 14)= 1.00000E-30 FLC( 15)= 1.00000E-30 FLC( 16)= 1.00000E-30 FLC( 17)= 1.00000E-30 FLC( 18)= 1.00000E-30 FLC( 19)= 1.00000E-30 FLC( 20)= 1.00000E-30 FLC( 21)= 1.00000E-30 FLC( 22)= 1.00000E-30 FLC( 23)=-6.00000E+00 FLC( 24)=-4.00000E+00 FLC( 25)=-2.00000E+00 FLC( 26)= 0.00000E+00 FLC( 27)= 2.00000E+00 FLC( 28)= 4.00000E+00 FLC( 29)= 8.00000E+00 FLC( 30)= 1.20000E+01 FLC( 31)= 1.60000E+01 FLC( 32)= 2.00000E+01 FLC( 33)= 2.40000E+01 FLC( 34)= 1.00000E-30 FLC( 35)= 1.00000E-30 FLC( 36)= 1.00000E-30 FLC( 37)= 1.00000E-30 FLC( 38)= 1.00000E-30 FLC( 39)= 1.00000E-30 FLC( 40)= 1.00000E-30 FLC( 41)= 1.00000E-30 FLC( 42)= 1.00000E-30 FLC( 43)= 4.28000E+06 FLC( 44)= 1.00000E-30 FLC( 45)= 1.00000E-30 FLC( 46)= 1.00000E-30 FLC( 47)= 1.00000E-30 FLC( 48)= 1.00000E-30 FLC( 49)= 1.00000E-30 FLC( 50)= 1.00000E-30 FLC( 51)= 1.00000E-30 FLC( 52)= 1.00000E-30 FLC( 53)= 1.00000E-30 FLC( 54)= 1.00000E-30 FLC( 55)= 1.00000E-30 FLC( 56)= 1.00000E-30 FLC( 57)= 1.00000E-30 FLC( 58)= 1.00000E-30 FLC( 59)= 1.00000E-30 FLC( 60)= 1.00000E-30 FLC( 61)= 1.00000E-30 FLC( 62)= 1.00000E-30 FLC( 63)= 1.00000E-30 FLC( 64)= 1.00000E-30 FLC( 65)= 1.00000E-30 FLC( 66)= 1.00000E-30 FLC( 67)= 1.00000E-30 FLC( 68)= 1.00000E-30 FLC( 69)= 1.00000E-30 FLC( 70)= 1.00000E-30 FLC( 71)= 1.00000E-30 FLC( 72)= 1.00000E-30 FLC( 73)= 1.00000E-30 FLC( 74)=-1.00000E-30 FLC( 75)= 1.00000E-30 FLC( 76)= 1.00000E-30 FLC( 77)= 1.00000E-30 FLC( 78)= 1.00000E-30 FLC( 79)= 1.00000E-30 FLC( 80)= 1.00000E-30 FLC( 81)= 1.00000E-30 FLC( 82)= 1.00000E-30 FLC( 83)= 1.00000E-30 FLC( 84)= 1.00000E-30 FLC( 85)= 1.00000E-30 FLC( 86)= 1.00000E-30 FLC( 87)= 1.00000E-30 FLC( 88)= 1.00000E-30 FLC( 89)= 1.00000E-30 FLC( 90)= 1.00000E-30 FLC( 91)= 1.00000E-30 FLC( 92)= 1.00000E-30 FLC( 93)= 1.00000E-30 FLC( 94)= 6.00000E-01 FLC( 95)= 1.40000E+00 FLC( 96)= 0.00000E+00 FLC( 97)=-1.00000E-30 FLC( 98)= 1.00000E-30 FLC( 99)= 1.00000E-30 FLC(100)= 1.00000E-30 FLC(101)= 1.00000E-30 FLC(102)= 1.00000E-30 FLC(103)= 1.00000E-30 FLC(104)= 1.00000E-30 FLC(105)= 1.00000E-30 FLC(106)= 1.00000E-30 FLC(107)= 1.00000E-30 FLC(108)= 1.00000E-30 FLC(109)= 1.00000E-30 FLC(110)= 1.00000E-30 FLC(111)= 1.00000E-30 FLC(112)= 1.00000E-30 FLC(113)= 1.00000E-30 FLC(114)= 1.00000E-30 FLC(115)= 1.00000E-30 FLC(116)= 1.00000E-30 FLC(117)=-1.00000E-30 FLC(118)= 1.00000E-30 FLC(119)= 1.00000E-30 FLC(120)= 1.00000E-30 FLC(121)= 1.00000E-30 FLC(122)= 1.00000E-30 FLC(123)= 1.00000E-30 FLC(124)= 1.00000E-30 FLC(125)= 1.00000E-30 FLC(126)= 1.00000E-30 FLC(127)= 1.00000E-30 FLC(128)= 1.00000E-30 FLC(129)= 1.00000E-30 FLC(130)= 1.00000E-30 FLC(131)= 1.00000E-30 FLC(132)= 1.00000E-30 FLC(133)= 1.00000E-30 FLC(134)= 1.00000E-30 FLC(135)= 1.00000E-30 FLC(136)= 1.00000E-30 FLC(137)=-1.00000E-30 FLC(138)= 1.00000E-30 FLC(139)= 1.00000E-30 FLC(140)= 1.00000E-30 FLC(141)= 1.00000E-30 FLC(142)= 1.00000E-30 FLC(143)= 1.00000E-30 FLC(144)= 1.00000E-30 FLC(145)= 1.00000E-30 FLC(146)= 1.00000E-30 FLC(147)= 1.00000E-30 FLC(148)= 1.00000E-30 FLC(149)= 1.00000E-30 FLC(150)= 1.00000E-30 FLC(151)= 1.00000E-30 FLC(152)= 1.00000E-30 FLC(153)= 1.00000E-30 FLC(154)= 1.00000E-30 FLC(155)= 1.00000E-30 FLC(156)= 1.00000E-30 FLC(157)= 1.00000E-30 FLC(158)= 1.00000E-30 FLC(159)= 0.00000E+00 FLC(160)= 1.00000E+00 OPTI( 1)= 8.85000E+00 OPTI( 2)= 2.46000E+00 OPTI( 3)= 1.60000E-04 OPTI( 4)= 4.28000E+00 SYNA( 1)= 4.14000E+00 SYNA( 2)= 1.00000E-30 SYNA( 3)= 1.00000E-30 SYNA( 4)= 1.00000E-30 SYNA( 5)=-2.00000E-01 SYNA( 6)= 1.00000E-30 SYNA( 7)= 1.00000E-30 SYNA( 8)= 1.00000E-30 SYNA( 9)= 1.00000E-30 SYNA( 10)= NaN SYNA( 11)= 1.00000E-30 SYNA( 12)= 1.00000E-30 SYNA( 13)= 1.00000E+00 SYNA( 14)= 1.00000E-30 SYNA( 15)= 1.00000E-30 SYNA( 16)= 1.00000E-30 SYNA( 17)= 1.00000E-30 SYNA( 18)= 1.00000E-30 SYNA( 19)= 1.00000E-30 BDIN( 1)= 1.00000E+01 BDIN( 2)= 0.00000E+00 BDIN( 3)= 2.58000E-01 BDIN( 4)= 5.89000E-01 BDIN( 5)= 1.26000E+00 BDIN( 6)= 2.26000E+00 BDIN( 7)= 2.59000E+00 BDIN( 8)= 2.93000E+00 BDIN( 9)= 3.59000E+00 BDIN( 10)= 4.57000E+00 BDIN( 11)= 6.26000E+00 BDIN( 12)= 1.00000E-30 BDIN( 13)= 1.00000E-30 BDIN( 14)= 1.00000E-30 BDIN( 15)= 1.00000E-30 BDIN( 16)= 1.00000E-30 BDIN( 17)= 1.00000E-30 BDIN( 18)= 1.00000E-30 BDIN( 19)= 1.00000E-30 BDIN( 20)= 1.00000E-30 BDIN( 21)= 1.00000E-30 BDIN( 22)= 0.00000E+00 BDIN( 23)= 8.00000E-02 BDIN( 24)= 1.60000E-01 BDIN( 25)= 3.23000E-01 BDIN( 26)= 7.51000E-01 BDIN( 27)= 8.83000E-01 BDIN( 28)= 9.39000E-01 BDIN( 29)= 1.03200E+00 BDIN( 30)= 1.03200E+00 BDIN( 31)= 1.03200E+00 BDIN( 32)= 1.00000E-30 BDIN( 33)= 1.00000E-30 BDIN( 34)= 1.00000E-30 BDIN( 35)= 1.00000E-30 BDIN( 36)= 1.00000E-30 BDIN( 37)= 1.00000E-30 BDIN( 38)= 1.00000E-30 BDIN( 39)= 1.00000E-30 BDIN( 40)= 1.00000E-30 BDIN( 41)= 1.00000E-30 BDIN( 42)= 0.00000E+00 BDIN( 43)= 1.00000E+00 BDIN( 44)= 1.42000E+00 BDIN( 45)= 2.01000E+00 BDIN( 46)= 3.08000E+00 BDIN( 47)= 3.34000E+00 BDIN( 48)= 3.44000E+00 BDIN( 49)= 3.61000E+00 BDIN( 50)= 3.61000E+00 BDIN( 51)= 3.61000E+00 BDIN( 52)= 1.00000E-30 BDIN( 53)= 1.00000E-30 BDIN( 54)= 1.00000E-30 BDIN( 55)= 1.00000E-30 BDIN( 56)= 1.00000E-30 BDIN( 57)= 1.00000E-30 BDIN( 58)= 1.00000E-30 BDIN( 59)= 1.00000E-30 BDIN( 60)= 1.00000E-30 BDIN( 61)= 1.00000E-30 BDIN( 62)= 0.00000E+00 BDIN( 63)= 1.86000E-01 BDIN( 64)= 2.86000E-01 BDIN( 65)= 4.24000E-01 BDIN( 66)= 5.33000E-01 BDIN( 67)= 5.33000E-01 BDIN( 68)= 5.33000E-01 BDIN( 69)= 5.33000E-01 BDIN( 70)= 5.33000E-01 BDIN( 71)= 5.33000E-01 BDIN( 72)= 1.00000E-30 BDIN( 73)= 1.00000E-30 BDIN( 74)= 1.00000E-30 BDIN( 75)= 1.00000E-30 BDIN( 76)= 1.00000E-30 BDIN( 77)= 1.00000E-30 BDIN( 78)= 1.00000E-30 BDIN( 79)= 1.00000E-30 BDIN( 80)= 1.00000E-30 BDIN( 81)= 1.00000E-30 BDIN( 82)= 1.00000E-30 BDIN( 83)= 1.00000E-30 BDIN( 84)= 1.00000E-30 BDIN( 85)= 1.00000E-30 BDIN( 86)= 1.00000E-30 BDIN( 87)= 1.00000E-30 BDIN( 88)= 1.00000E-30 BDIN( 89)= 1.00000E-30 BDIN( 90)= 1.00000E-30 BDIN( 91)= 1.00000E-30 BDIN( 92)= 1.00000E-30 BDIN( 93)= 1.00000E-30 BDIN( 94)= 1.00000E-30 BDIN( 95)= 1.00000E-30 BDIN( 96)= 1.00000E-30 BDIN( 97)= 1.00000E-30 BDIN( 98)= 1.00000E-30 BDIN( 99)= 1.00000E-30 BDIN(100)= 1.00000E-30 BDIN(101)= 1.00000E-30 BDIN(102)= 1.00000E-30 BDIN(103)= 1.00000E-30 BDIN(104)= 1.00000E-30 BDIN(105)= 1.00000E-30 BDIN(106)= 1.00000E-30 BDIN(107)= 1.00000E-30 BDIN(108)= 1.00000E-30 BDIN(109)= 1.00000E-30 BDIN(110)= 1.00000E-30 BDIN(111)= 1.00000E-30 BDIN(112)= 1.00000E-30 BDIN(113)= 1.00000E-30 BDIN(114)= 1.00000E-30 BDIN(115)= 1.00000E-30 BDIN(116)= 1.00000E-30 BDIN(117)= 1.00000E-30 BDIN(118)= 1.00000E-30 BDIN(119)= 1.00000E-30 BDIN(120)= 1.00000E-30 BDIN(121)= 1.00000E-30 BDIN(122)= 1.00000E+00 BDIN(123)= 1.00000E-30 BDIN(124)= 2.59000E+00 BDIN(125)= 3.67000E+00 BDIN(126)= 1.00000E-30 BDIN(127)= 2.00000E+00 BDIN(128)= 1.00000E+00 BDIN(129)= 1.00000E+00 0**** FOLLOWING ARE THE IOM DATA BLOCKS **** BODY( 1)= 2.29591E-02 BODY( 2)= 2.17639E-02 BODY( 3)= 2.10455E-02 BODY( 4)= 2.08059E-02 BODY( 5)= 2.10455E-02 BODY( 6)= 2.17639E-02 BODY( 7)= 2.46284E-02 BODY( 8)= 2.93715E-02 BODY( 9)= 3.59470E-02 BODY( 10)= 4.42904E-02 BODY( 11)= 5.43198E-02 BODY( 12)= 1.00000E-30 BODY( 13)= 1.00000E-30 BODY( 14)= 1.00000E-30 BODY( 15)= 1.00000E-30 BODY( 16)= 1.00000E-30 BODY( 17)= 1.00000E-30 BODY( 18)= 1.00000E-30 BODY( 19)= 1.00000E-30 BODY( 20)= 1.00000E-30 BODY( 21)=-2.05992E-02 BODY( 22)=-1.37328E-02 BODY( 23)=-6.86641E-03 BODY( 24)= 0.00000E+00 BODY( 25)= 6.86641E-03 BODY( 26)= 1.37328E-02 BODY( 27)= 2.74656E-02 BODY( 28)= 4.11985E-02 BODY( 29)= 5.49313E-02 BODY( 30)= 6.86641E-02 BODY( 31)= 8.23969E-02 BODY( 32)= 1.00000E-30 BODY( 33)= 1.00000E-30 BODY( 34)= 1.00000E-30 BODY( 35)= 1.00000E-30 BODY( 36)= 1.00000E-30 BODY( 37)= 1.00000E-30 BODY( 38)= 1.00000E-30 BODY( 39)= 1.00000E-30 BODY( 40)= 1.00000E-30 BODY( 41)=-2.06577E-02 BODY( 42)=-1.37718E-02 BODY( 43)=-6.88590E-03 BODY( 44)= 0.00000E+00 BODY( 45)= 6.88590E-03 BODY( 46)= 1.37718E-02 BODY( 47)= 2.75436E-02 BODY( 48)= 4.13154E-02 BODY( 49)= 5.50872E-02 BODY( 50)= 6.88590E-02 BODY( 51)= 8.26307E-02 BODY( 52)= 1.00000E-30 BODY( 53)= 1.00000E-30 BODY( 54)= 1.00000E-30 BODY( 55)= 1.00000E-30 BODY( 56)= 1.00000E-30 BODY( 57)= 1.00000E-30 BODY( 58)= 1.00000E-30 BODY( 59)= 1.00000E-30 BODY( 60)= 1.00000E-30 BODY( 61)=-2.28863E-02 BODY( 62)=-1.52175E-02 BODY( 63)=-7.59671E-03 BODY( 64)= 0.00000E+00 BODY( 65)= 7.59671E-03 BODY( 66)= 1.52175E-02 BODY( 67)= 3.06260E-02 BODY( 68)= 4.64049E-02 BODY( 69)= 6.27117E-02 BODY( 70)= 7.96714E-02 BODY( 71)= 9.73672E-02 BODY( 72)= 1.00000E-30 BODY( 73)= 1.00000E-30 BODY( 74)= 1.00000E-30 BODY( 75)= 1.00000E-30 BODY( 76)= 1.00000E-30 BODY( 77)= 1.00000E-30 BODY( 78)= 1.00000E-30 BODY( 79)= 1.00000E-30 BODY( 80)= 1.00000E-30 BODY( 81)= 2.06801E-02 BODY( 82)= 2.07529E-02 BODY( 83)= 2.07931E-02 BODY( 84)= 2.08059E-02 BODY( 85)= 2.07931E-02 BODY( 86)= 2.07529E-02 BODY( 87)= 2.05662E-02 BODY( 88)= 2.01641E-02 BODY( 89)= 1.94134E-02 BODY( 90)= 1.81349E-02 BODY( 91)= 1.61097E-02 BODY( 92)= 1.00000E-30 BODY( 93)= 1.00000E-30 BODY( 94)= 1.00000E-30 BODY( 95)= 1.00000E-30 BODY( 96)= 1.00000E-30 BODY( 97)= 1.00000E-30 BODY( 98)= 1.00000E-30 BODY( 99)= 1.00000E-30 BODY(100)= 1.00000E-30 BODY(101)= 3.43321E-03 BODY(102)= 3.43321E-03 BODY(103)= 3.43321E-03 BODY(104)= 3.43321E-03 BODY(105)= 3.43321E-03 BODY(106)= 3.43321E-03 BODY(107)= 3.43321E-03 BODY(108)= 3.43321E-03 BODY(109)= 3.43321E-03 BODY(110)= 3.43321E-03 BODY(111)= 3.43321E-03 BODY(112)= 1.00000E-30 BODY(113)= 1.00000E-30 BODY(114)= 1.00000E-30 BODY(115)= 1.00000E-30 BODY(116)= 1.00000E-30 BODY(117)= 1.00000E-30 BODY(118)= 1.00000E-30 BODY(119)= 1.00000E-30 BODY(120)= 1.00000E-30 BODY(121)= 3.44295E-03 BODY(122)= 3.44295E-03 BODY(123)= 3.44295E-03 BODY(124)= 3.44295E-03 BODY(125)= 3.44295E-03 BODY(126)= 3.44295E-03 BODY(127)= 3.44295E-03 BODY(128)= 3.44295E-03 BODY(129)= 3.44295E-03 BODY(130)= 3.44295E-03 BODY(131)= 3.44295E-03 BODY(132)= 1.00000E-30 BODY(133)= 1.00000E-30 BODY(134)= 1.00000E-30 BODY(135)= 1.00000E-30 BODY(136)= 1.00000E-30 BODY(137)= 1.00000E-30 BODY(138)= 1.00000E-30 BODY(139)= 1.00000E-30 BODY(140)= 1.00000E-30 BODY(141)=-3.43321E-03 BODY(142)=-3.43321E-03 BODY(143)=-3.43321E-03 BODY(144)=-3.43321E-03 BODY(145)=-3.43321E-03 BODY(146)=-3.43321E-03 BODY(147)=-3.43321E-03 BODY(148)=-3.43321E-03 BODY(149)=-3.43321E-03 BODY(150)=-3.43321E-03 BODY(151)=-3.43321E-03 BODY(152)= 1.00000E-30 BODY(153)= 1.00000E-30 BODY(154)= 1.00000E-30 BODY(155)= 1.00000E-30 BODY(156)= 1.00000E-30 BODY(157)= 1.00000E-30 BODY(158)= 1.00000E-30 BODY(159)= 1.00000E-30 BODY(160)= 1.00000E-30 BODY(161)=-1.97889E-03 BODY(162)=-1.97889E-03 BODY(163)=-1.97889E-03 BODY(164)=-1.97889E-03 BODY(165)=-1.97889E-03 BODY(166)=-1.97889E-03 BODY(167)=-1.97889E-03 BODY(168)=-1.97889E-03 BODY(169)=-1.97889E-03 BODY(170)=-1.97889E-03 BODY(171)=-1.97889E-03 BODY(172)= 1.00000E-30 BODY(173)= 1.00000E-30 BODY(174)= 1.00000E-30 BODY(175)= 1.00000E-30 BODY(176)= 1.00000E-30 BODY(177)= 1.00000E-30 BODY(178)= 1.00000E-30 BODY(179)= 1.00000E-30 BODY(180)= 1.00000E-30 BODY(181)= 0.00000E+00 BODY(182)= 0.00000E+00 BODY(183)= 0.00000E+00 BODY(184)= 0.00000E+00 BODY(185)= 0.00000E+00 BODY(186)= 0.00000E+00 BODY(187)= 0.00000E+00 BODY(188)= 0.00000E+00 BODY(189)= 0.00000E+00 BODY(190)= 0.00000E+00 BODY(191)= 0.00000E+00 BODY(192)= 1.00000E-30 BODY(193)= 1.00000E-30 BODY(194)= 1.00000E-30 BODY(195)= 1.00000E-30 BODY(196)= 1.00000E-30 BODY(197)= 1.00000E-30 BODY(198)= 1.00000E-30 BODY(199)= 1.00000E-30 BODY(200)= 1.00000E-30 BODY(201)= 1.00000E-30 BODY(202)= 1.00000E-30 BODY(203)= 1.00000E-30 BODY(204)= 1.00000E-30 BODY(205)= 1.00000E-30 BODY(206)= 1.00000E-30 BODY(207)= 1.00000E-30 BODY(208)= 1.00000E-30 BODY(209)= 1.00000E-30 BODY(210)= 1.00000E-30 BODY(211)= 1.00000E-30 BODY(212)= 1.00000E-30 BODY(213)= 1.00000E-30 BODY(214)= 1.00000E-30 BODY(215)= 1.00000E-30 BODY(216)= 1.00000E-30 BODY(217)= 1.00000E-30 BODY(218)= 1.00000E-30 BODY(219)= 1.00000E-30 BODY(220)= 1.00000E-30 BODY(221)= 1.00000E-30 BODY(222)= 1.00000E-30 BODY(223)= 1.00000E-30 BODY(224)= 1.00000E-30 BODY(225)= 1.00000E-30 BODY(226)= 1.00000E-30 BODY(227)= 1.00000E-30 BODY(228)= 1.00000E-30 BODY(229)= 1.00000E-30 BODY(230)= 1.00000E-30 BODY(231)= 1.00000E-30 BODY(232)= 1.00000E-30 BODY(233)= 1.00000E-30 BODY(234)= 1.00000E-30 BODY(235)= 1.00000E-30 BODY(236)= 1.00000E-30 BODY(237)= 1.00000E-30 BODY(238)= 1.00000E-30 BODY(239)= 1.00000E-30 BODY(240)= 1.00000E-30 BODY(241)= 1.00000E-30 BODY(242)= 1.00000E-30 BODY(243)= 1.00000E-30 BODY(244)= 1.00000E-30 BODY(245)= 1.00000E-30 BODY(246)= 1.00000E-30 BODY(247)= 1.00000E-30 BODY(248)= 1.00000E-30 BODY(249)= 1.00000E-30 BODY(250)= 1.00000E-30 BODY(251)= 1.00000E-30 BODY(252)= 1.00000E-30 BODY(253)= 1.00000E-30 BODY(254)= 1.00000E-30 BODY(255)= 1.00000E-30 BODY(256)= 1.00000E-30 BODY(257)= 1.00000E-30 BODY(258)= 1.00000E-30 BODY(259)= 1.00000E-30 BODY(260)= 1.00000E-30 BODY(261)= 1.00000E-30 BODY(262)= 1.00000E-30 BODY(263)= 1.00000E-30 BODY(264)= 1.00000E-30 BODY(265)= 1.00000E-30 BODY(266)= 1.00000E-30 BODY(267)= 1.00000E-30 BODY(268)= 1.00000E-30 BODY(269)= 1.00000E-30 BODY(270)= 1.00000E-30 BODY(271)= 1.00000E-30 BODY(272)= 1.00000E-30 BODY(273)= 1.00000E-30 BODY(274)= 1.00000E-30 BODY(275)= 1.00000E-30 BODY(276)= 1.00000E-30 BODY(277)= 1.00000E-30 BODY(278)= 1.00000E-30 BODY(279)= 1.00000E-30 BODY(280)= 1.00000E-30 BODY(281)= 1.00000E-30 BODY(282)= 1.00000E-30 BODY(283)= 1.00000E-30 BODY(284)= 1.00000E-30 BODY(285)= 1.00000E-30 BODY(286)= 1.00000E-30 BODY(287)= 1.00000E-30 BODY(288)= 1.00000E-30 BODY(289)= 1.00000E-30 BODY(290)= 1.00000E-30 BODY(291)= 1.00000E-30 BODY(292)= 1.00000E-30 BODY(293)= 1.00000E-30 BODY(294)= 1.00000E-30 BODY(295)= 1.00000E-30 BODY(296)= 1.00000E-30 BODY(297)= 1.00000E-30 BODY(298)= 1.00000E-30 BODY(299)= 1.00000E-30 BODY(300)= 1.00000E-30 BODY(301)= 1.00000E-30 BODY(302)= 1.00000E-30 BODY(303)= 1.00000E-30 BODY(304)= 1.00000E-30 BODY(305)= 1.00000E-30 BODY(306)= 1.00000E-30 BODY(307)= 1.00000E-30 BODY(308)= 1.00000E-30 BODY(309)= 1.00000E-30 BODY(310)= 1.00000E-30 BODY(311)= 1.00000E-30 BODY(312)= 1.00000E-30 BODY(313)= 1.00000E-30 BODY(314)= 1.00000E-30 BODY(315)= 1.00000E-30 BODY(316)= 1.00000E-30 BODY(317)= 1.00000E-30 BODY(318)= 1.00000E-30 BODY(319)= 1.00000E-30 BODY(320)= 1.00000E-30 BODY(321)= 1.00000E-30 BODY(322)= 1.00000E-30 BODY(323)= 1.00000E-30 BODY(324)= 1.00000E-30 BODY(325)= 1.00000E-30 BODY(326)= 1.00000E-30 BODY(327)= 1.00000E-30 BODY(328)= 1.00000E-30 BODY(329)= 1.00000E-30 BODY(330)= 1.00000E-30 BODY(331)= 1.00000E-30 BODY(332)= 1.00000E-30 BODY(333)= 1.00000E-30 BODY(334)= 1.00000E-30 BODY(335)= 1.00000E-30 BODY(336)= 1.00000E-30 BODY(337)= 1.00000E-30 BODY(338)= 1.00000E-30 BODY(339)= 1.00000E-30 BODY(340)= 1.00000E-30 BODY(341)= 1.00000E-30 BODY(342)= 1.00000E-30 BODY(343)= 1.00000E-30 BODY(344)= 1.00000E-30 BODY(345)= 1.00000E-30 BODY(346)= 1.00000E-30 BODY(347)= 1.00000E-30 BODY(348)= 1.00000E-30 BODY(349)= 1.00000E-30 BODY(350)= 1.00000E-30 BODY(351)= 1.00000E-30 BODY(352)= 1.00000E-30 BODY(353)= 1.00000E-30 BODY(354)= 1.00000E-30 BODY(355)= 1.00000E-30 BODY(356)= 1.00000E-30 BODY(357)= 1.00000E-30 BODY(358)= 1.00000E-30 BODY(359)= 1.00000E-30 BODY(360)= 1.00000E-30 BODY(361)= 1.00000E-30 BODY(362)= 1.00000E-30 BODY(363)= 1.00000E-30 BODY(364)= 1.00000E-30 BODY(365)= 1.00000E-30 BODY(366)= 1.00000E-30 BODY(367)= 1.00000E-30 BODY(368)= 1.00000E-30 BODY(369)= 1.00000E-30 BODY(370)= 1.00000E-30 BODY(371)= 1.00000E-30 BODY(372)= 1.00000E-30 BODY(373)= 1.00000E-30 BODY(374)= 1.00000E-30 BODY(375)= 1.00000E-30 BODY(376)= 1.00000E-30 BODY(377)= 1.00000E-30 BODY(378)= 1.00000E-30 BODY(379)= 1.00000E-30 BODY(380)= 1.00000E-30 BODY(381)= 1.00000E-30 BODY(382)= 1.00000E-30 BODY(383)= 1.00000E-30 BODY(384)= 1.00000E-30 BODY(385)= 1.00000E-30 BODY(386)= 1.00000E-30 BODY(387)= 1.00000E-30 BODY(388)= 1.00000E-30 BODY(389)= 1.00000E-30 BODY(390)= 1.00000E-30 BODY(391)= 1.00000E-30 BODY(392)= 1.00000E-30 BODY(393)= 1.00000E-30 BODY(394)= 1.00000E-30 BODY(395)= 1.00000E-30 BODY(396)= 1.00000E-30 BODY(397)= 1.00000E-30 BODY(398)= 1.00000E-30 BODY(399)= 1.00000E-30 BODY(400)= 1.00000E-30 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP DATCOM BODY ALONE CONFIGURATION APPROXIMATE AXISYMMETRIC BODY SOLUTION, EXAMPLE PROBLEM 1, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 4.2800E+06 8.850 2.460 4.280 4.140 -0.200 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -6.0 0.023 -0.021 -0.0207 -0.023 0.021 0.903 3.433E-03 3.443E-03 -3.433E-03 -1.979E-03 0.000E+00 -4.0 0.022 -0.014 -0.0138 -0.015 0.021 0.905 3.433E-03 3.443E-03 -3.433E-03 -1.979E-03 0.000E+00 -2.0 0.021 -0.007 -0.0069 -0.008 0.021 0.906 3.433E-03 3.443E-03 -3.433E-03 -1.979E-03 0.000E+00 0.0 0.021 0.000 0.0000 0.000 0.021 ****** 3.433E-03 3.443E-03 -3.433E-03 -1.979E-03 0.000E+00 2.0 0.021 0.007 0.0069 0.008 0.021 0.906 3.433E-03 3.443E-03 -3.433E-03 -1.979E-03 0.000E+00 4.0 0.022 0.014 0.0138 0.015 0.021 0.905 3.433E-03 3.443E-03 -3.433E-03 -1.979E-03 0.000E+00 8.0 0.025 0.027 0.0275 0.031 0.021 0.899 3.433E-03 3.443E-03 -3.433E-03 -1.979E-03 0.000E+00 12.0 0.029 0.041 0.0413 0.046 0.020 0.890 3.433E-03 3.443E-03 -3.433E-03 -1.979E-03 0.000E+00 16.0 0.036 0.055 0.0551 0.063 0.019 0.878 3.433E-03 3.443E-03 -3.433E-03 -1.979E-03 0.000E+00 20.0 0.044 0.069 0.0689 0.080 0.018 0.864 3.433E-03 3.443E-03 -3.433E-03 -1.979E-03 0.000E+00 24.0 0.054 0.082 0.0826 0.097 0.016 0.849 3.433E-03 3.443E-03 -3.433E-03 -1.979E-03 0.000E+00 1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE. 0 $BODY ZU(1)=-.595,-.476,-.372,-.138,0.200,.334,.343,.343,.343,.343, ZL(1)=-.595,-.715,-.754,-.805,-.868,-.868,-.868,-.868,-.868,-.868$ CASEID ASYMMETRIC (CAMBERED) BODY SOLUTION, EXAMPLE PROBLEM 1, CASE 2 SAVE NEXT CASE 0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP DATCOM BODY ALONE CONFIGURATION ASYMMETRIC (CAMBERED) BODY SOLUTION, EXAMPLE PROBLEM 1, CASE 2 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 4.2800E+06 8.850 2.460 4.280 4.140 -0.200 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -6.0 0.022 -0.012 -0.0239 -0.014 0.021 1.651 3.227E-03 4.111E-03 -3.227E-03 -2.363E-03 0.000E+00 -4.0 0.021 -0.007 -0.0157 -0.008 0.021 1.951 2.837E-03 4.092E-03 -2.837E-03 -2.352E-03 0.000E+00 -2.0 0.021 -0.001 -0.0075 -0.002 0.021 4.654 2.859E-03 4.107E-03 -2.859E-03 -2.360E-03 0.000E+00 0.0 0.021 0.005 0.0007 0.005 0.021 0.147 2.853E-03 4.102E-03 -2.853E-03 -2.357E-03 0.000E+00 2.0 0.021 0.011 0.0089 0.011 0.021 0.790 2.818E-03 4.077E-03 -2.818E-03 -2.343E-03 0.000E+00 4.0 0.022 0.016 0.0170 0.018 0.021 0.965 2.751E-03 4.029E-03 -2.751E-03 -2.315E-03 0.000E+00 8.0 0.026 0.027 0.0329 0.030 0.022 1.093 2.537E-03 3.874E-03 -2.537E-03 -2.227E-03 0.000E+00 12.0 0.031 0.036 0.0480 0.042 0.022 1.144 2.233E-03 3.651E-03 -2.233E-03 -2.098E-03 0.000E+00 16.0 0.037 0.045 0.0621 0.053 0.023 1.171 3.100E-03 3.731E-03 -3.100E-03 -2.144E-03 0.000E+00 20.0 0.048 0.061 0.0779 0.074 0.024 1.054 6.089E-03 4.440E-03 -6.089E-03 -2.552E-03 0.000E+00 24.0 0.070 0.093 0.0976 0.114 0.026 0.859 9.984E-03 5.440E-03 -9.984E-03 -3.127E-03 0.000E+00 1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE. 0 $FLTCON NMACH=3.0,MACH(1)=0.90,1.40,2.5,RNNUB(1)=6.4E6,9.96E6,17.8E6$ SAVE CASEID ASYMMETRIC (CAMBERED) BODY SOLUTION, EXAMPLE PROBLEM 1, CASE 3 NEXT CASE 0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP DATCOM BODY ALONE CONFIGURATION ASYMMETRIC (CAMBERED) BODY SOLUTION, EXAMPLE PROBLEM 1, CASE 3 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.900 6.4000E+06 8.850 2.460 4.280 4.140 -0.200 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -6.0 NDM NDM NDM NDM NDM 1.003 3.433E-03 3.443E-03 -3.433E-03 -1.979E-03 0.000E+00 -4.0 NDM 0.000E+00 -2.0 NDM 0.000E+00 0.0 NDM 0.000E+00 2.0 NDM 0.000E+00 4.0 NDM 0.000E+00 8.0 NDM 0.000E+00 12.0 NDM 0.000E+00 16.0 NDM 0.000E+00 20.0 NDM 0.000E+00 24.0 NDM 0.000E+00 0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CONFIGURATION AUXILIARY AND PARTIAL OUTPUT DATCOM BODY ALONE CONFIGURATION ASYMMETRIC (CAMBERED) BODY SOLUTION, EXAMPLE PROBLEM 1, CASE 3 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.900 6.4000E+06 8.850 2.460 4.280 4.140 -0.200 BASIC BODY PROPERTIES WETTED AREA XCG ZCG BASE AREA ZERO LIFT DRAG BASE DRAG FRICTION DRAG PRESSURE DRAG 0.1837E+02 4.14 -0.20 1.0320 NDM NDM NDM NDM 0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST 1 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP DATCOM BODY ALONE CONFIGURATION ASYMMETRIC (CAMBERED) BODY SOLUTION, EXAMPLE PROBLEM 1, CASE 3 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 1.400 9.9600E+06 8.850 2.460 4.280 4.140 -0.200 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -6.0 0.041 -0.034 -0.0262 -0.039 0.037 0.680 7.070E-03 4.625E-03 -7.070E-03 -2.658E-03 0.000E+00 -4.0 0.039 -0.021 -0.0171 -0.024 0.037 0.718 6.202E-03 4.461E-03 -6.202E-03 -2.564E-03 0.000E+00 -2.0 0.038 -0.010 -0.0084 -0.011 0.037 0.762 5.305E-03 4.284E-03 -5.305E-03 -2.462E-03 0.000E+00 0.0 0.037 0.000 0.0000 0.000 0.037 ****** 4.842E-03 4.189E-03 -4.842E-03 -2.408E-03 0.000E+00 2.0 0.038 0.010 0.0084 0.011 0.037 0.762 5.305E-03 4.284E-03 -5.305E-03 -2.462E-03 0.000E+00 4.0 0.039 0.021 0.0171 0.024 0.037 0.718 6.191E-03 4.456E-03 -6.191E-03 -2.561E-03 0.000E+00 8.0 0.044 0.049 0.0356 0.055 0.037 0.647 7.795E-03 4.734E-03 -7.795E-03 -2.721E-03 0.000E+00 12.0 0.054 0.084 0.0550 0.093 0.036 0.591 9.347E-03 4.973E-03 -9.347E-03 -2.858E-03 0.000E+00 16.0 0.071 0.124 0.0754 0.139 0.034 0.542 1.110E-02 5.247E-03 -1.110E-02 -3.016E-03 0.000E+00 20.0 0.098 0.172 0.0970 0.195 0.033 0.496 1.318E-02 5.615E-03 -1.318E-02 -3.227E-03 0.000E+00 24.0 0.136 0.230 0.1203 0.265 0.031 0.454 1.542E-02 6.035E-03 -1.542E-02 -3.469E-03 0.000E+00 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP DATCOM BODY ALONE CONFIGURATION ASYMMETRIC (CAMBERED) BODY SOLUTION, EXAMPLE PROBLEM 1, CASE 3 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 2.500 1.7800E+07 8.850 2.460 4.280 4.140 -0.200 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -6.0 0.027 -0.039 -0.0224 -0.041 0.022 0.542 7.792E-03 4.008E-03 -7.792E-03 -2.304E-03 0.000E+00 -4.0 0.024 -0.024 -0.0146 -0.026 0.023 0.567 6.925E-03 3.834E-03 -6.925E-03 -2.204E-03 0.000E+00 -2.0 0.023 -0.011 -0.0071 -0.012 0.023 0.595 6.032E-03 3.651E-03 -6.032E-03 -2.098E-03 0.000E+00 0.0 0.023 0.000 0.0000 0.000 0.023 ****** 5.572E-03 3.554E-03 -5.572E-03 -2.043E-03 0.000E+00 2.0 0.023 0.011 0.0071 0.012 0.023 0.595 6.032E-03 3.651E-03 -6.032E-03 -2.098E-03 0.000E+00 4.0 0.024 0.024 0.0146 0.026 0.023 0.567 6.943E-03 3.837E-03 -6.943E-03 -2.205E-03 0.000E+00 8.0 0.030 0.056 0.0307 0.059 0.022 0.518 9.088E-03 4.268E-03 -9.088E-03 -2.453E-03 0.000E+00 12.0 0.043 0.097 0.0487 0.104 0.022 0.470 1.231E-02 4.940E-03 -1.231E-02 -2.839E-03 0.000E+00 16.0 0.066 0.154 0.0702 0.166 0.021 0.422 1.513E-02 5.549E-03 -1.513E-02 -3.189E-03 0.000E+00 20.0 0.101 0.218 0.0931 0.239 0.020 0.389 1.524E-02 5.576E-03 -1.524E-02 -3.205E-03 0.000E+00 24.0 0.144 0.276 0.1148 0.310 0.019 0.370 1.378E-02 5.253E-03 -1.378E-02 -3.019E-03 0.000E+00 1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE. 0 $FLTCON NMACH=1.0,MACH(1)=2.5,RNNUB(1)=17.86E6,HYPERS=.TRUE.$ $BODY DS=0.0$ CASEID HYPERSONIC BODY SOLUTION, EXAMPLE PROBLEM 1, CASE 4 NEXT CASE 0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP DATCOM BODY ALONE CONFIGURATION HYPERSONIC BODY SOLUTION, EXAMPLE PROBLEM 1, CASE 4 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 2.500 1.7860E+07 8.850 2.460 4.280 4.140 -0.200 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -6.0 0.016 -0.020 -0.0203 -0.022 0.014 0.923 4.413E-03 3.375E-03 -4.413E-03 -1.940E-03 0.000E+00 -4.0 0.014 -0.012 -0.0136 -0.013 0.013 1.022 3.744E-03 3.379E-03 -3.744E-03 -1.942E-03 0.000E+00 -2.0 0.013 -0.005 -0.0068 -0.006 0.013 1.144 3.075E-03 3.390E-03 -3.075E-03 -1.949E-03 0.000E+00 0.0 0.013 0.000 0.0000 0.000 0.013 ****** 2.741E-03 3.400E-03 -2.741E-03 -1.954E-03 0.000E+00 2.0 0.013 0.005 0.0068 0.006 0.013 1.144 3.075E-03 3.390E-03 -3.075E-03 -1.949E-03 0.000E+00 4.0 0.014 0.012 0.0136 0.013 0.013 1.022 3.736E-03 3.376E-03 -3.736E-03 -1.940E-03 0.000E+00 8.0 0.019 0.030 0.0270 0.032 0.014 0.841 4.961E-03 3.346E-03 -4.961E-03 -1.923E-03 0.000E+00 12.0 0.027 0.052 0.0403 0.056 0.016 0.714 6.037E-03 3.352E-03 -6.037E-03 -1.926E-03 0.000E+00 16.0 0.041 0.078 0.0538 0.086 0.018 0.624 6.927E-03 3.427E-03 -6.927E-03 -1.970E-03 0.000E+00 20.0 0.060 0.107 0.0677 0.121 0.020 0.558 7.539E-03 3.525E-03 -7.539E-03 -2.026E-03 0.000E+00 24.0 0.086 0.138 0.0820 0.161 0.022 0.508 7.992E-03 3.622E-03 -7.992E-03 -2.082E-03 0.000E+00 1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE. 0 $FLTCON NMACH=4.0,MACH(1)=0.60,0.90,1.40,2.50,LOOP=1.,NALT=4.0, ALT(1)=0.,2000.,40000.,90000.,HYPERS=.FALSE., NALPHA=11.,ALSCHD(1)=-6.0,-4.0,-2.0,0.0,2.0,4.0,8.0,12.0,16.0,20.0,24.0$ $OPTINS SREF=8.85,CBARR=2.46,BLREF=4.28$ $SYNTHS XW=3.61,ZW=-.80,ALIW=2.0,XCG=4.14$ $WGPLNF CHRDTP=0.64,SSPNE=1.59,SSPN=1.59,CHRDR=2.90,SAVSI=55.0,CHSTAT=0.0, TWISTA=0.0,SSPNDD=0.0,DHDADI=0.0,DHDADO=0.0,TYPE=1.0$ $WGSCHR DELTAY=2.85,XOVC=0.40,CLI=0.127,ALPHAI=0.123,CLALPA(1)=.1335, TOVC=0.11,CLMAXL=1.55, CLMAX(1)=1.195,CMO=-.0262,LERI=.0134,CAMBER=.TRUE.,CLAMO=.105,TCEFF=0.055$ CASEID STRAIGHT TAPERED EXPOSED WING SOLUTION, EXAMPLE PROBLEM 2, CASE 1 SAVE DUMP A NEXT CASE 0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000 A( 1)= 5.62860E+00 A( 2)= 1.28000E-30 A( 3)= 5.62860E+00 A( 4)= 5.62860E+00 A( 5)= 1.79661E+00 A( 6)= 1.00000E+00 A( 7)= 1.79661E+00 A( 8)= 1.00000E-30 A( 9)= 1.00000E-30 A( 10)= 2.90000E+00 A( 11)= 1.00000E-30 A( 12)= 1.00000E-30 A( 13)= 1.00000E-30 A( 14)= 1.00000E-30 A( 15)= 2.01047E+00 A( 16)= 2.01047E+00 A( 17)= 6.40000E-01 A( 18)= 7.83019E-01 A( 19)= 1.00000E+00 A( 20)= 1.00000E-30 A( 21)= 1.59000E+00 A( 22)= 1.00000E-30 A( 23)= 1.59000E+00 A( 24)= 1.00000E-30 A( 25)= 2.20690E-01 A( 26)= 2.20690E-01 A( 27)= 2.20690E-01 A( 28)= 1.00000E+00 A( 29)= 2.91075E+00 A( 30)= 1.89900E+00 A( 31)= 6.25819E-01 A( 32)= 6.25819E-01 A( 33)= 1.59000E+00 A( 34)= 5.50000E+01 A( 35)= 9.59931E-01 A( 36)= 8.19152E-01 A( 37)= 5.73577E-01 A( 38)= 1.42815E+00 A( 39)= 9.59931E-01 A( 40)= 4.70115E+01 A( 41)= 8.20506E-01 A( 42)= 7.31491E-01 A( 43)= 6.81851E-01 A( 44)= 1.07280E+00 A( 45)= 8.20506E-01 A( 46)= 3.56578E+01 A( 47)= 6.22345E-01 A( 48)= 5.82942E-01 A( 49)= 8.12514E-01 A( 50)= 7.17456E-01 A( 51)= 6.22345E-01 A( 52)= 3.87545E-01 A( 53)= 6.76394E-03 A( 54)= 6.76366E-03 A( 55)= 9.99977E-01 A( 56)= 6.76382E-03 A( 57)= 6.76394E-03 A( 58)= 5.50000E+01 A( 59)= 9.59931E-01 A( 60)= 8.19152E-01 A( 61)= 5.73577E-01 A( 62)= 1.42815E+00 A( 63)= 9.59931E-01 A( 64)= 4.70115E+01 A( 65)= 8.20506E-01 A( 66)= 7.31491E-01 A( 67)= 6.81851E-01 A( 68)= 1.07280E+00 A( 69)= 8.20506E-01 A( 70)= 3.56578E+01 A( 71)= 6.22345E-01 A( 72)= 5.82942E-01 A( 73)= 8.12514E-01 A( 74)= 7.17456E-01 A( 75)= 6.22345E-01 A( 76)= 3.87545E-01 A( 77)= 6.76394E-03 A( 78)= 6.76366E-03 A( 79)= 9.99977E-01 A( 80)= 6.76382E-03 A( 81)= 6.76394E-03 A( 82)= 0.00000E+00 A( 83)= 0.00000E+00 A( 84)= 0.00000E+00 A( 85)= 1.00000E+00 A( 86)= 0.00000E+00 A( 87)= 0.00000E+00 A( 88)= 0.00000E+00 A( 89)= 0.00000E+00 A( 90)= 0.00000E+00 A( 91)= 1.00000E+00 A( 92)= 0.00000E+00 A( 93)= 0.00000E+00 A( 94)= 0.00000E+00 A( 95)= 0.00000E+00 A( 96)= 0.00000E+00 A( 97)= 1.00000E+00 A( 98)= 0.00000E+00 A( 99)= 0.00000E+00 A(100)= 0.00000E+00 A(101)= 0.00000E+00 A(102)= 0.00000E+00 A(103)= 1.00000E+00 A(104)= 0.00000E+00 A(105)= 0.00000E+00 A(106)= 5.50000E+01 A(107)= 9.59931E-01 A(108)= 8.19152E-01 A(109)= 5.73577E-01 A(110)= 1.42815E+00 A(111)= 9.59931E-01 A(112)= 0.00000E+00 A(113)= 0.00000E+00 A(114)= 0.00000E+00 A(115)= 1.00000E+00 A(116)= 0.00000E+00 A(117)= 0.00000E+00 A(118)= 2.20690E-01 A(119)= 5.62860E+00 A(120)= 1.79661E+00 A(121)= 2.01047E+00 A(122)= 2.01047E+00 A(123)= 4.75379E-01 A(124)= 8.46243E-01 A(125)= 4.13593E+00 A(126)=-1.08652E+00 A(127)= 2.85598E+01 A(128)= 3.50000E+00 A(129)= 4.24094E+06 A(130)= 6.25819E-01 A(131)= 1.33500E-01 A(132)= 1.19500E+00 A(133)= 0.00000E+00 A(134)=-8.28311E-01 A(135)= 1.00000E-30 A(136)= 6.25819E-01 A(137)= 1.00000E+00 A(138)= 0.00000E+00 A(139)= 0.00000E+00 A(140)= 0.00000E+00 A(141)= 1.00000E+00 A(142)= 0.00000E+00 A(143)= 0.00000E+00 A(144)= 6.32750E+00 A(145)= 5.90000E-01 A(146)= 1.00000E-30 A(147)= 2.63384E+01 A(148)= 4.59692E-01 A(149)= 4.43672E-01 A(150)= 8.96189E-01 A(151)= 4.95065E-01 A(152)= 4.59692E-01 A(153)= 2.68220E+01 A(154)= 4.68132E-01 A(155)= 4.51220E-01 A(156)= 8.92412E-01 A(157)= 5.05619E-01 A(158)= 4.68132E-01 A(159)= 5.82759E-01 A(160)= 4.06108E+00 A(161)= 1.39638E+00 A(162)= 1.00000E+00 A(163)= 1.79661E+00 A(164)= 7.95000E-01 A(165)= 7.95000E-01 A(166)= 1.00000E-30 A(167)= 1.00000E-30 A(168)= 1.00000E-30 A(169)= 1.00000E-30 A(170)= 1.82759E-01 A(171)= 1.00000E-30 A(172)= 1.00000E-30 A(173)= 5.30000E-01 A(174)= 4.00000E-01 A(175)= 4.06822E+01 A(176)= 7.10038E-01 A(177)= 6.51862E-01 A(178)= 7.58337E-01 A(179)= 8.59594E-01 A(180)= 7.10038E-01 A(181)= 0.00000E+00 A(182)= 0.00000E+00 A(183)= 0.00000E+00 A(184)= 1.00000E+00 A(185)= 0.00000E+00 A(186)= 0.00000E+00 A(187)= 4.06822E+01 A(188)= 7.10038E-01 A(189)= 6.51862E-01 A(190)= 7.58337E-01 A(191)= 8.59594E-01 A(192)= 7.10038E-01 A(193)= 1.00000E-30 A(194)= 1.00000E-30 A(195)= 8.93762E-01 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING ALONE CONFIGURATION STRAIGHT TAPERED EXPOSED WING SOLUTION, EXAMPLE PROBLEM 2, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 0.00 669.80 2.1162E+03 518.670 4.2409E+06 8.850 2.460 4.280 4.140 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -6.0 0.007 -0.087 0.0264 -0.087 -0.002 -0.303 2.602E-02 -9.884E-03 2.199E-05 1.127E-05 3.984E-04 -4.0 0.005 -0.031 0.0073 -0.031 0.003 -0.233 2.715E-02 -9.689E-03 2.387E-06 1.401E-06 1.428E-04 -2.0 0.005 0.022 -0.0124 0.022 0.006 -0.571 2.704E-02 -1.043E-02 2.005E-06 8.039E-07 -1.004E-04 0.0 0.006 0.077 -0.0344 0.077 0.006 -0.447 2.836E-02 -1.171E-02 2.080E-05 9.483E-06 -3.540E-04 2.0 0.010 0.135 -0.0592 0.136 0.005 -0.437 2.975E-02 -1.295E-02 6.210E-05 2.911E-05 -6.216E-04 4.0 0.016 0.196 -0.0862 0.197 0.002 -0.438 3.083E-02 -1.364E-02 1.289E-04 6.116E-05 -9.007E-04 8.0 0.036 0.323 -0.1419 0.325 -0.010 -0.437 3.049E-02 -1.404E-02 3.468E-04 1.658E-04 -1.484E-03 12.0 0.062 0.440 -0.1985 0.443 -0.031 -0.448 2.598E-02 -1.361E-02 6.502E-04 3.092E-04 -2.021E-03 16.0 0.088 0.531 -0.2508 0.534 -0.062 -0.469 1.839E-02 -1.175E-02 9.638E-04 4.542E-04 -2.438E-03 20.0 0.107 0.587 -0.2925 0.588 -0.101 -0.497 9.285E-03 -8.734E-03 1.213E-03 5.624E-04 -2.697E-03 24.0 0.113 0.605 -0.3207 0.599 -0.143 -0.536 -3.121E-04 -5.360E-03 1.331E-03 6.070E-04 -2.780E-03 A( 1)= 5.62860E+00 A( 2)= 1.28000E-30 A( 3)= 5.62860E+00 A( 4)= 5.62860E+00 A( 5)= 1.79661E+00 A( 6)= 1.00000E+00 A( 7)= 1.79661E+00 A( 8)= 1.00000E-30 A( 9)= 1.00000E-30 A( 10)= 2.90000E+00 A( 11)= 1.00000E-30 A( 12)= 1.00000E-30 A( 13)= 1.00000E-30 A( 14)= 1.00000E-30 A( 15)= 2.01047E+00 A( 16)= 2.01047E+00 A( 17)= 6.40000E-01 A( 18)= 7.83019E-01 A( 19)= 1.00000E+00 A( 20)= 1.00000E-30 A( 21)= 1.59000E+00 A( 22)= 1.00000E-30 A( 23)= 1.59000E+00 A( 24)= 1.00000E-30 A( 25)= 2.20690E-01 A( 26)= 2.20690E-01 A( 27)= 2.20690E-01 A( 28)= 1.00000E+00 A( 29)= 2.91075E+00 A( 30)= 1.89900E+00 A( 31)= 6.25819E-01 A( 32)= 6.25819E-01 A( 33)= 1.59000E+00 A( 34)= 5.50000E+01 A( 35)= 9.59931E-01 A( 36)= 8.19152E-01 A( 37)= 5.73577E-01 A( 38)= 1.42815E+00 A( 39)= 9.59931E-01 A( 40)= 4.70115E+01 A( 41)= 8.20506E-01 A( 42)= 7.31491E-01 A( 43)= 6.81851E-01 A( 44)= 1.07280E+00 A( 45)= 8.20506E-01 A( 46)= 3.56578E+01 A( 47)= 6.22345E-01 A( 48)= 5.82942E-01 A( 49)= 8.12514E-01 A( 50)= 7.17456E-01 A( 51)= 6.22345E-01 A( 52)= 3.87545E-01 A( 53)= 6.76394E-03 A( 54)= 6.76366E-03 A( 55)= 9.99977E-01 A( 56)= 6.76382E-03 A( 57)= 6.76394E-03 A( 58)= 5.50000E+01 A( 59)= 9.59931E-01 A( 60)= 8.19152E-01 A( 61)= 5.73577E-01 A( 62)= 1.42815E+00 A( 63)= 9.59931E-01 A( 64)= 4.70115E+01 A( 65)= 8.20506E-01 A( 66)= 7.31491E-01 A( 67)= 6.81851E-01 A( 68)= 1.07280E+00 A( 69)= 8.20506E-01 A( 70)= 3.56578E+01 A( 71)= 6.22345E-01 A( 72)= 5.82942E-01 A( 73)= 8.12514E-01 A( 74)= 7.17456E-01 A( 75)= 6.22345E-01 A( 76)= 3.87545E-01 A( 77)= 6.76394E-03 A( 78)= 6.76366E-03 A( 79)= 9.99977E-01 A( 80)= 6.76382E-03 A( 81)= 6.76394E-03 A( 82)= 0.00000E+00 A( 83)= 0.00000E+00 A( 84)= 0.00000E+00 A( 85)= 1.00000E+00 A( 86)= 1.00000E-05 A( 87)= 0.00000E+00 A( 88)= 0.00000E+00 A( 89)= 0.00000E+00 A( 90)= 0.00000E+00 A( 91)= 1.00000E+00 A( 92)= 0.00000E+00 A( 93)= 0.00000E+00 A( 94)= 0.00000E+00 A( 95)= 0.00000E+00 A( 96)= 0.00000E+00 A( 97)= 1.00000E+00 A( 98)= 0.00000E+00 A( 99)= 0.00000E+00 A(100)= 0.00000E+00 A(101)= 0.00000E+00 A(102)= 0.00000E+00 A(103)= 1.00000E+00 A(104)= 0.00000E+00 A(105)= 0.00000E+00 A(106)= 5.50000E+01 A(107)= 9.59931E-01 A(108)= 8.19152E-01 A(109)= 5.73577E-01 A(110)= 1.42815E+00 A(111)= 9.59931E-01 A(112)= 0.00000E+00 A(113)= 0.00000E+00 A(114)= 0.00000E+00 A(115)= 1.00000E+00 A(116)= 0.00000E+00 A(117)= 0.00000E+00 A(118)= 2.20690E-01 A(119)= 5.62860E+00 A(120)= 1.79661E+00 A(121)= 2.01047E+00 A(122)= 2.01047E+00 A(123)= 4.75379E-01 A(124)= 8.46243E-01 A(125)= 4.13593E+00 A(126)=-1.08652E+00 A(127)= 2.85598E+01 A(128)= 3.50000E+00 A(129)= 6.02051E+06 A(130)= 6.25819E-01 A(131)= 1.31250E-01 A(132)= 1.55000E+00 A(133)= 0.00000E+00 A(134)=-8.44619E-01 A(135)= 1.00000E-30 A(136)= 6.25819E-01 A(137)= 1.00000E+00 A(138)= 0.00000E+00 A(139)= 0.00000E+00 A(140)= 0.00000E+00 A(141)= 1.00000E+00 A(142)= 0.00000E+00 A(143)= 0.00000E+00 A(144)= 6.32750E+00 A(145)= 5.90000E-01 A(146)= 1.00000E-30 A(147)= 2.63547E+01 A(148)= 4.59976E-01 A(149)= 4.43927E-01 A(150)= 8.96063E-01 A(151)= 4.95419E-01 A(152)= 4.59976E-01 A(153)= 2.68382E+01 A(154)= 4.68415E-01 A(155)= 4.51472E-01 A(156)= 8.92285E-01 A(157)= 5.05973E-01 A(158)= 4.68415E-01 A(159)= 5.82759E-01 A(160)= 4.06108E+00 A(161)= 1.39638E+00 A(162)= 1.00000E+00 A(163)= 1.79661E+00 A(164)= 7.95000E-01 A(165)= 7.95000E-01 A(166)= 1.00000E-30 A(167)= 1.00000E-30 A(168)= 1.00000E-30 A(169)= 1.00000E-30 A(170)= 1.82759E-01 A(171)= 1.00000E-30 A(172)= 1.00000E-30 A(173)= 5.30000E-01 A(174)= 4.00000E-01 A(175)= 4.06822E+01 A(176)= 7.10038E-01 A(177)= 6.51862E-01 A(178)= 7.58337E-01 A(179)= 8.59594E-01 A(180)= 7.10038E-01 A(181)= 0.00000E+00 A(182)= 0.00000E+00 A(183)= 0.00000E+00 A(184)= 1.00000E+00 A(185)= 0.00000E+00 A(186)= 0.00000E+00 A(187)= 4.06822E+01 A(188)= 7.10038E-01 A(189)= 6.51862E-01 A(190)= 7.58337E-01 A(191)= 8.59594E-01 A(192)= 7.10038E-01 A(193)= 1.00000E-30 A(194)= 1.00000E-30 A(195)= 8.93762E-01 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING ALONE CONFIGURATION STRAIGHT TAPERED EXPOSED WING SOLUTION, EXAMPLE PROBLEM 2, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.900 2000.00 997.76 1.9677E+03 511.538 6.0205E+06 8.850 2.460 4.280 4.140 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -6.0 0.004 NDM NDM NDM NDM -0.440 2.645E-02 -1.163E-02 NDM NDM NDM -4.0 NDM -2.0 NDM 0.0 NDM 2.0 NDM 4.0 NDM 8.0 NDM 12.0 NDM 16.0 NDM 20.0 NDM 24.0 NDM 0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CONFIGURATION AUXILIARY AND PARTIAL OUTPUT WING ALONE CONFIGURATION STRAIGHT TAPERED EXPOSED WING SOLUTION, EXAMPLE PROBLEM 2, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.900 2000.00 997.76 1.9677E+03 511.538 6.0205E+06 8.850 2.460 4.280 4.140 0.000 XCG RELATIVE TO THEORETICAL LEADING EDGE MAC= -0.36 BASIC PLANFORM PROPERTIES TAPER ASPECT QUARTER CHORD QUARTER CHORD ZERO LIFT FRICTION AREA RATIO RATIO SWEEP MAC X(MAC) Y(MAC) DRAG COEFFICIENT 0 WING TOTAL THEORITICAL + 0.5629E+01 0.221 0.1797E+01 47.012 0.201E+01 0.501E+01 0.626E+00 TOTAL EXPOSED + 0.5629E+01 0.221 0.1797E+01 47.012 0.201E+01 0.501E+01 0.626E+00 0.418E-02 0.283E-02 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CONFIGURATION AUXILIARY AND PARTIAL OUTPUT WING ALONE CONFIGURATION STRAIGHT TAPERED EXPOSED WING SOLUTION, EXAMPLE PROBLEM 2, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.900 2000.00 997.76 1.9677E+03 511.538 6.0205E+06 8.850 2.460 4.280 4.140 0.000 *** WING DATA FAIRING *** CDL/CL**2 = 0.3584E+00 CLB/CL =-0.3941E-02 FORCE BREAK MACH NUMBER (ZERO SWEEP) = 0.9474E+00 FORCE BREAK MACH NUMBER (WITH SWEEP) = 0.9620E+00 MACH(A) = 1.032 CLA(A) = 0.2266E-01 MACH(B) = 1.102 CLA(B) = 0.2162E-01 (CLB/CL)M=0.6 =-0.4594E-02 (CLB/CL)M=1.4 =-0.2097E-02 LIFT-CURVE-SLOPE INTERPOLATION TABLE MACH CL-ALPHA 0.750 0.2660E-01 0.962 0.2544E-01 1.032 0.2266E-01 1.102 0.2162E-01 1.400 0.2414E-01 1 A( 1)= 5.62860E+00 A( 2)= 1.28000E-30 A( 3)= 5.62860E+00 A( 4)= 5.62860E+00 A( 5)= 1.79661E+00 A( 6)= 1.00000E+00 A( 7)= 1.79661E+00 A( 8)= 1.00000E-30 A( 9)= 1.00000E-30 A( 10)= 2.90000E+00 A( 11)= 1.00000E-30 A( 12)= 1.00000E-30 A( 13)= 1.00000E-30 A( 14)= 1.00000E-30 A( 15)= 2.01047E+00 A( 16)= 2.01047E+00 A( 17)= 6.40000E-01 A( 18)= 7.83019E-01 A( 19)= 1.00000E+00 A( 20)= 1.00000E-30 A( 21)= 1.59000E+00 A( 22)= 1.00000E-30 A( 23)= 1.59000E+00 A( 24)= 1.00000E-30 A( 25)= 2.20690E-01 A( 26)= 2.20690E-01 A( 27)= 2.20690E-01 A( 28)= 1.00000E+00 A( 29)= 2.91075E+00 A( 30)= 1.89900E+00 A( 31)= 6.25819E-01 A( 32)= 6.25819E-01 A( 33)= 1.59000E+00 A( 34)= 5.50000E+01 A( 35)= 9.59931E-01 A( 36)= 8.19152E-01 A( 37)= 5.73577E-01 A( 38)= 1.42815E+00 A( 39)= 9.59931E-01 A( 40)= 4.70115E+01 A( 41)= 8.20506E-01 A( 42)= 7.31491E-01 A( 43)= 6.81851E-01 A( 44)= 1.07280E+00 A( 45)= 8.20506E-01 A( 46)= 3.56578E+01 A( 47)= 6.22345E-01 A( 48)= 5.82942E-01 A( 49)= 8.12514E-01 A( 50)= 7.17456E-01 A( 51)= 6.22345E-01 A( 52)= 3.87545E-01 A( 53)= 6.76394E-03 A( 54)= 6.76366E-03 A( 55)= 9.99977E-01 A( 56)= 6.76382E-03 A( 57)= 6.76394E-03 A( 58)= 5.50000E+01 A( 59)= 9.59931E-01 A( 60)= 8.19152E-01 A( 61)= 5.73577E-01 A( 62)= 1.42815E+00 A( 63)= 9.59931E-01 A( 64)= 4.70115E+01 A( 65)= 8.20506E-01 A( 66)= 7.31491E-01 A( 67)= 6.81851E-01 A( 68)= 1.07280E+00 A( 69)= 8.20506E-01 A( 70)= 3.56578E+01 A( 71)= 6.22345E-01 A( 72)= 5.82942E-01 A( 73)= 8.12514E-01 A( 74)= 7.17456E-01 A( 75)= 6.22345E-01 A( 76)= 3.87545E-01 A( 77)= 6.76394E-03 A( 78)= 6.76366E-03 A( 79)= 9.99977E-01 A( 80)= 6.76382E-03 A( 81)= 6.76394E-03 A( 82)= 0.00000E+00 A( 83)= 0.00000E+00 A( 84)= 0.00000E+00 A( 85)= 1.00000E+00 A( 86)= 0.00000E+00 A( 87)= 0.00000E+00 A( 88)= 0.00000E+00 A( 89)= 0.00000E+00 A( 90)= 0.00000E+00 A( 91)= 1.00000E+00 A( 92)= 0.00000E+00 A( 93)= 0.00000E+00 A( 94)= 0.00000E+00 A( 95)= 0.00000E+00 A( 96)= 0.00000E+00 A( 97)= 1.00000E+00 A( 98)= 0.00000E+00 A( 99)= 0.00000E+00 A(100)= 0.00000E+00 A(101)= 0.00000E+00 A(102)= 0.00000E+00 A(103)= 1.00000E+00 A(104)= 0.00000E+00 A(105)= 0.00000E+00 A(106)= 5.50000E+01 A(107)= 9.59931E-01 A(108)= 8.19152E-01 A(109)= 5.73577E-01 A(110)= 1.42815E+00 A(111)= 9.59931E-01 A(112)= 0.00000E+00 A(113)= 0.00000E+00 A(114)= 0.00000E+00 A(115)= 1.00000E+00 A(116)= 0.00000E+00 A(117)= 0.00000E+00 A(118)= 2.20690E-01 A(119)= 5.62860E+00 A(120)= 1.79661E+00 A(121)= 2.01047E+00 A(122)= 2.01047E+00 A(123)= 4.75379E-01 A(124)= 8.46243E-01 A(125)= 4.13593E+00 A(126)=-1.08652E+00 A(127)= 2.85598E+01 A(128)= 3.50000E+00 A(129)= 2.66828E+06 A(130)= 6.25819E-01 A(131)= 1.31250E-01 A(132)= 1.55000E+00 A(133)= 0.00000E+00 A(134)=-8.44619E-01 A(135)= 1.00000E-30 A(136)= 6.25819E-01 A(137)= 1.00000E+00 A(138)= 0.00000E+00 A(139)= 0.00000E+00 A(140)= 0.00000E+00 A(141)= 1.00000E+00 A(142)= 0.00000E+00 A(143)= 0.00000E+00 A(144)= 6.32750E+00 A(145)= 5.90000E-01 A(146)= 1.00000E-30 A(147)= 2.63547E+01 A(148)= 4.59976E-01 A(149)= 4.43927E-01 A(150)= 8.96063E-01 A(151)= 4.95419E-01 A(152)= 4.59976E-01 A(153)= 2.68382E+01 A(154)= 4.68415E-01 A(155)= 4.51472E-01 A(156)= 8.92285E-01 A(157)= 5.05973E-01 A(158)= 4.68415E-01 A(159)= 5.82759E-01 A(160)= 4.06108E+00 A(161)= 1.39638E+00 A(162)= 1.00000E+00 A(163)= 1.79661E+00 A(164)= 7.95000E-01 A(165)= 7.95000E-01 A(166)= 1.00000E-30 A(167)= 1.00000E-30 A(168)= 1.00000E-30 A(169)= 1.00000E-30 A(170)= 1.82759E-01 A(171)= 1.00000E-30 A(172)= 1.00000E-30 A(173)= 5.30000E-01 A(174)= 4.00000E-01 A(175)= 4.06822E+01 A(176)= 7.10038E-01 A(177)= 6.51862E-01 A(178)= 7.58337E-01 A(179)= 8.59594E-01 A(180)= 7.10038E-01 A(181)= 0.00000E+00 A(182)= 0.00000E+00 A(183)= 0.00000E+00 A(184)= 1.00000E+00 A(185)= 0.00000E+00 A(186)= 0.00000E+00 A(187)= 4.06822E+01 A(188)= 7.10038E-01 A(189)= 6.51862E-01 A(190)= 7.58337E-01 A(191)= 8.59594E-01 A(192)= 7.10038E-01 A(193)= 1.00000E-30 A(194)= 1.00000E-30 A(195)= 8.93762E-01 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING ALONE CONFIGURATION STRAIGHT TAPERED EXPOSED WING SOLUTION, EXAMPLE PROBLEM 2, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 1.400 40000.00 1355.16 3.9312E+02 389.970 2.6683E+06 8.850 2.460 4.280 4.140 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -6.0 0.019 -0.102 0.0482 -0.103 0.008 -0.466 2.414E-02 -1.205E-02 NDM NDM 2.141E-04 -4.0 0.015 -0.050 0.0241 -0.051 0.011 -0.476 2.551E-02 1.048E-04 -2.0 0.013 0.000 0.0000 0.000 0.013 0.000 2.488E-02 9.597E-07 0.0 0.015 0.050 -0.0241 0.050 0.015 -0.485 2.551E-02 -1.030E-04 2.0 0.019 0.102 -0.0482 0.103 0.015 -0.470 2.659E-02 -2.124E-04 4.0 0.026 0.156 -0.0723 0.158 0.015 -0.459 2.728E-02 -3.261E-04 8.0 0.051 0.267 -0.1205 0.272 0.013 -0.444 2.764E-02 -5.621E-04 12.0 0.088 0.377 NDM 0.387 0.008 2.677E-02 -8.016E-04 16.0 0.135 0.481 NDM 0.500 -0.003 2.466E-02 -1.035E-03 20.0 0.187 0.575 NDM 0.604 -0.021 2.146E-02 -1.250E-03 24.0 0.238 0.653 NDM 0.693 -0.049 1.775E-02 -1.435E-03 0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST A( 1)= 5.62860E+00 A( 2)= 1.28000E-30 A( 3)= 5.62860E+00 A( 4)= 5.62860E+00 A( 5)= 1.79661E+00 A( 6)= 1.00000E+00 A( 7)= 1.79661E+00 A( 8)= 1.00000E-30 A( 9)= 1.00000E-30 A( 10)= 2.90000E+00 A( 11)= 1.00000E-30 A( 12)= 1.00000E-30 A( 13)= 1.00000E-30 A( 14)= 1.00000E-30 A( 15)= 2.01047E+00 A( 16)= 2.01047E+00 A( 17)= 6.40000E-01 A( 18)= 7.83019E-01 A( 19)= 1.00000E+00 A( 20)= 1.00000E-30 A( 21)= 1.59000E+00 A( 22)= 1.00000E-30 A( 23)= 1.59000E+00 A( 24)= 1.00000E-30 A( 25)= 2.20690E-01 A( 26)= 2.20690E-01 A( 27)= 2.20690E-01 A( 28)= 1.00000E+00 A( 29)= 2.91075E+00 A( 30)= 1.89900E+00 A( 31)= 6.25819E-01 A( 32)= 6.25819E-01 A( 33)= 1.59000E+00 A( 34)= 5.50000E+01 A( 35)= 9.59931E-01 A( 36)= 8.19152E-01 A( 37)= 5.73577E-01 A( 38)= 1.42815E+00 A( 39)= 9.59931E-01 A( 40)= 4.70115E+01 A( 41)= 8.20506E-01 A( 42)= 7.31491E-01 A( 43)= 6.81851E-01 A( 44)= 1.07280E+00 A( 45)= 8.20506E-01 A( 46)= 3.56578E+01 A( 47)= 6.22345E-01 A( 48)= 5.82942E-01 A( 49)= 8.12514E-01 A( 50)= 7.17456E-01 A( 51)= 6.22345E-01 A( 52)= 3.87545E-01 A( 53)= 6.76394E-03 A( 54)= 6.76366E-03 A( 55)= 9.99977E-01 A( 56)= 6.76382E-03 A( 57)= 6.76394E-03 A( 58)= 5.50000E+01 A( 59)= 9.59931E-01 A( 60)= 8.19152E-01 A( 61)= 5.73577E-01 A( 62)= 1.42815E+00 A( 63)= 9.59931E-01 A( 64)= 4.70115E+01 A( 65)= 8.20506E-01 A( 66)= 7.31491E-01 A( 67)= 6.81851E-01 A( 68)= 1.07280E+00 A( 69)= 8.20506E-01 A( 70)= 3.56578E+01 A( 71)= 6.22345E-01 A( 72)= 5.82942E-01 A( 73)= 8.12514E-01 A( 74)= 7.17456E-01 A( 75)= 6.22345E-01 A( 76)= 3.87545E-01 A( 77)= 6.76394E-03 A( 78)= 6.76366E-03 A( 79)= 9.99977E-01 A( 80)= 6.76382E-03 A( 81)= 6.76394E-03 A( 82)= 0.00000E+00 A( 83)= 0.00000E+00 A( 84)= 0.00000E+00 A( 85)= 1.00000E+00 A( 86)= 0.00000E+00 A( 87)= 0.00000E+00 A( 88)= 0.00000E+00 A( 89)= 0.00000E+00 A( 90)= 0.00000E+00 A( 91)= 1.00000E+00 A( 92)= 0.00000E+00 A( 93)= 0.00000E+00 A( 94)= 0.00000E+00 A( 95)= 0.00000E+00 A( 96)= 0.00000E+00 A( 97)= 1.00000E+00 A( 98)= 0.00000E+00 A( 99)= 0.00000E+00 A(100)= 0.00000E+00 A(101)= 0.00000E+00 A(102)= 0.00000E+00 A(103)= 1.00000E+00 A(104)= 0.00000E+00 A(105)= 0.00000E+00 A(106)= 5.50000E+01 A(107)= 9.59931E-01 A(108)= 8.19152E-01 A(109)= 5.73577E-01 A(110)= 1.42815E+00 A(111)= 9.59931E-01 A(112)= 0.00000E+00 A(113)= 0.00000E+00 A(114)= 0.00000E+00 A(115)= 1.00000E+00 A(116)= 0.00000E+00 A(117)= 0.00000E+00 A(118)= 2.20690E-01 A(119)= 5.62860E+00 A(120)= 1.79661E+00 A(121)= 2.01047E+00 A(122)= 2.01047E+00 A(123)= 4.75379E-01 A(124)= 8.46243E-01 A(125)= 4.13593E+00 A(126)=-1.08652E+00 A(127)= 2.85598E+01 A(128)= 3.50000E+00 A(129)= 4.26445E+05 A(130)= 6.25819E-01 A(131)= 1.31250E-01 A(132)= 1.55000E+00 A(133)= 0.00000E+00 A(134)=-8.44619E-01 A(135)= 1.00000E-30 A(136)= 6.25819E-01 A(137)= 1.00000E+00 A(138)= 0.00000E+00 A(139)= 0.00000E+00 A(140)= 0.00000E+00 A(141)= 1.00000E+00 A(142)= 0.00000E+00 A(143)= 0.00000E+00 A(144)= 6.32750E+00 A(145)= 5.90000E-01 A(146)= 1.00000E-30 A(147)= 2.63547E+01 A(148)= 4.59976E-01 A(149)= 4.43927E-01 A(150)= 8.96063E-01 A(151)= 4.95419E-01 A(152)= 4.59976E-01 A(153)= 2.68382E+01 A(154)= 4.68415E-01 A(155)= 4.51472E-01 A(156)= 8.92285E-01 A(157)= 5.05973E-01 A(158)= 4.68415E-01 A(159)= 5.82759E-01 A(160)= 4.06108E+00 A(161)= 1.39638E+00 A(162)= 1.00000E+00 A(163)= 1.79661E+00 A(164)= 7.95000E-01 A(165)= 7.95000E-01 A(166)= 1.00000E-30 A(167)= 1.00000E-30 A(168)= 1.00000E-30 A(169)= 1.00000E-30 A(170)= 1.82759E-01 A(171)= 1.00000E-30 A(172)= 1.00000E-30 A(173)= 5.30000E-01 A(174)= 4.00000E-01 A(175)= 4.06822E+01 A(176)= 7.10038E-01 A(177)= 6.51862E-01 A(178)= 7.58337E-01 A(179)= 8.59594E-01 A(180)= 7.10038E-01 A(181)= 0.00000E+00 A(182)= 0.00000E+00 A(183)= 0.00000E+00 A(184)= 1.00000E+00 A(185)= 0.00000E+00 A(186)= 0.00000E+00 A(187)= 4.06822E+01 A(188)= 7.10038E-01 A(189)= 6.51862E-01 A(190)= 7.58337E-01 A(191)= 8.59594E-01 A(192)= 7.10038E-01 A(193)= 1.00000E-30 A(194)= 1.00000E-30 A(195)= 8.93762E-01 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING ALONE CONFIGURATION STRAIGHT TAPERED EXPOSED WING SOLUTION, EXAMPLE PROBLEM 2, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 2.500 90000.00 2460.43 3.6777E+01 403.136 4.2644E+05 8.850 2.460 4.280 4.140 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -6.0 0.018 -0.062 0.0316 -0.063 0.011 -0.497 1.453E-02 -7.892E-03 NDM NDM 7.719E-05 -4.0 0.015 -0.030 0.0158 -0.031 0.013 -0.507 1.548E-02 3.785E-05 -2.0 0.014 0.000 0.0000 0.000 0.014 0.000 1.508E-02 5.856E-07 0.0 0.015 0.030 -0.0158 0.030 0.015 -0.523 1.548E-02 -3.668E-05 2.0 0.018 0.062 -0.0316 0.063 0.016 -0.505 1.609E-02 -7.605E-05 4.0 0.023 0.095 -0.0473 0.096 0.016 -0.494 1.626E-02 -1.167E-04 8.0 0.040 0.159 -0.0789 0.163 0.017 -0.483 1.567E-02 -1.987E-04 12.0 0.064 0.220 NDM 0.228 0.017 1.425E-02 -2.778E-04 16.0 0.091 0.273 NDM 0.288 0.012 1.273E-02 -3.502E-04 20.0 0.121 0.322 NDM 0.344 0.004 1.204E-02 -4.180E-04 24.0 0.155 0.370 NDM 0.401 -0.009 1.193E-02 -4.876E-04 0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST 1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE. 0 $FLTCON NMACH=2.0,MACH(1)=0.60,2.5,LOOP=2.,NALT=2.,ALT(1)=0.,90000.$ $SYNTHS XW=2.497,ZW=-.71$ $WGPLNF SSPNOP=1.11,CHRDBP=2.24,CHRDR=4.01,SAVSI=75.1,SAVSO=55.0,TYPE=3.0$ $WGSCHR TOVC=.10,LERI=0.011,LERO=.0158,TOVCO=0.12,XOVCO=0.40,CMOT=-.0262$ CASEID EXPOSED CRANKED WING SOLUTION, EXAMPLE PROBLEM 2, CASE 2 SAVE NEXT CASE 0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000 0*** WARNING *** WING NOT STRAIGHT TAPERED. UNIFORM SECTION ASSUMED. 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING ALONE CONFIGURATION EXPOSED CRANKED WING SOLUTION, EXAMPLE PROBLEM 2, CASE 2 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 0.00 669.80 2.1162E+03 518.670 4.2409E+06 8.850 2.460 4.280 4.140 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -6.0 0.010 -0.119 0.0371 -0.120 -0.003 -0.310 2.983E-02 -1.109E-02 1.162E-04 4.044E-05 6.347E-04 -4.0 0.006 -0.060 0.0179 -0.060 0.002 -0.298 2.983E-02 -1.009E-02 2.906E-05 1.003E-05 3.173E-04 -2.0 0.005 0.000 -0.0032 0.000 0.005 18.814 2.983E-02 -1.107E-02 0.000E+00 0.000E+00 0.000E+00 0.0 0.006 0.060 -0.0264 0.060 0.006 -0.443 2.983E-02 -1.199E-02 2.906E-05 1.102E-05 -3.173E-04 2.0 0.010 0.119 -0.0512 0.120 0.005 -0.428 2.983E-02 -1.259E-02 1.162E-04 4.366E-05 -6.347E-04 4.0 0.020 0.179 -0.0768 0.180 0.007 -0.427 3.339E-02 -1.417E-02 2.615E-04 9.816E-05 -9.520E-04 8.0 0.091 0.341 -0.1444 0.350 0.043 -0.412 4.439E-02 -1.697E-02 9.247E-04 3.530E-04 -1.814E-03 12.0 0.146 0.534 -0.2126 0.553 0.031 -0.385 4.858E-02 -1.889E-02 2.235E-03 8.509E-04 -2.841E-03 16.0 0.225 0.730 -0.2955 0.763 0.015 -0.387 4.761E-02 -2.150E-02 4.147E-03 1.591E-03 -3.881E-03 20.0 0.323 0.915 -0.3846 0.970 -0.009 -0.396 4.468E-02 -2.421E-02 6.519E-03 2.516E-03 -4.866E-03 24.0 0.434 1.087 -0.4891 1.170 -0.046 -0.418 4.138E-02 -2.807E-02 9.234E-03 3.601E-03 -5.782E-03 0***NOTE*** CRANKED WING ANALYSIS PERFORMED EVEN THOUGH WING HAS A LOW ASPECT RATIO. 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING ALONE CONFIGURATION EXPOSED CRANKED WING SOLUTION, EXAMPLE PROBLEM 2, CASE 2 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 2.500 0.00 2790.81 2.1162E+03 518.670 1.7671E+07 8.850 2.460 4.280 4.140 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -6.0 0.011 NDM 0.0365 NDM 0.011 -0.491 1.859E-02 -9.124E-03 NDM NDM NDM -4.0 -2.0 0.0 2.0 4.0 8.0 12.0 16.0 20.0 24.0 0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST 0***NOTE*** CRANKED WING ANALYSIS PERFORMED EVEN THOUGH WING HAS A LOW ASPECT RATIO. 0** CD0= 1.050E-02 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING ALONE CONFIGURATION EXPOSED CRANKED WING SOLUTION, EXAMPLE PROBLEM 2, CASE 2 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 90000.00 590.50 3.6777E+01 403.136 1.0235E+05 8.850 2.460 4.280 4.140 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -6.0 0.018 -0.119 0.0371 -0.121 0.005 -0.308 2.983E-02 -1.109E-02 1.162E-04 4.039E-05 6.347E-04 -4.0 0.012 -0.060 0.0179 -0.060 0.007 -0.296 2.983E-02 -1.009E-02 2.906E-05 1.002E-05 3.173E-04 -2.0 0.010 0.000 -0.0032 0.000 0.010 9.597 2.983E-02 -1.107E-02 0.000E+00 0.000E+00 0.000E+00 0.0 0.012 0.060 -0.0264 0.060 0.012 -0.443 2.983E-02 -1.199E-02 2.906E-05 1.102E-05 -3.173E-04 2.0 0.018 0.119 -0.0512 0.120 0.013 -0.427 2.983E-02 -1.259E-02 1.162E-04 4.363E-05 -6.347E-04 4.0 0.032 0.179 -0.0768 0.181 0.020 -0.425 3.339E-02 -1.417E-02 2.615E-04 9.804E-05 -9.520E-04 8.0 0.123 0.341 -0.1444 0.355 0.075 -0.407 4.439E-02 -1.697E-02 9.247E-04 3.519E-04 -1.814E-03 12.0 0.217 0.534 -0.2126 0.568 0.101 -0.375 4.858E-02 -1.889E-02 2.235E-03 8.454E-04 -2.841E-03 16.0 0.354 0.730 -0.2955 0.799 0.140 -0.370 4.761E-02 -2.150E-02 4.147E-03 1.573E-03 -3.881E-03 20.0 0.524 0.915 -0.3846 1.039 0.179 -0.370 4.468E-02 -2.421E-02 6.519E-03 2.474E-03 -4.866E-03 24.0 0.715 1.087 -0.4891 1.284 0.211 -0.381 4.138E-02 -2.807E-02 9.234E-03 3.517E-03 -5.782E-03 0***NOTE*** CRANKED WING ANALYSIS PERFORMED EVEN THOUGH WING HAS A LOW ASPECT RATIO. 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING ALONE CONFIGURATION EXPOSED CRANKED WING SOLUTION, EXAMPLE PROBLEM 2, CASE 2 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 2.500 90000.00 2460.43 3.6777E+01 403.136 4.2644E+05 8.850 2.460 4.280 4.140 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -6.0 0.012 NDM 0.0365 NDM 0.012 -0.491 1.859E-02 -9.124E-03 NDM NDM NDM -4.0 -2.0 0.0 2.0 4.0 8.0 12.0 16.0 20.0 24.0 0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST 0***NOTE*** CRANKED WING ANALYSIS PERFORMED EVEN THOUGH WING HAS A LOW ASPECT RATIO. 0** CD0= 1.243E-02 1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE. 0 $FLTCON LOOP=3.$ $WGPLNF TYPE=2.0$ CASEID EXPOSED DOUBLE DELTA WING SOLUTION, EXAMPLE PROBLEM 2, CASE 3 NEXT CASE 0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000 0*** WARNING *** WING NOT STRAIGHT TAPERED. UNIFORM SECTION ASSUMED. 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING ALONE CONFIGURATION EXPOSED DOUBLE DELTA WING SOLUTION, EXAMPLE PROBLEM 2, CASE 3 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 0.00 669.80 2.1162E+03 518.670 4.2409E+06 8.850 2.460 4.280 4.140 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -6.0 0.014 -0.131 0.0410 -0.132 0.000 -0.312 2.448E-02 -9.096E-03 1.306E-04 4.864E-05 6.956E-04 -4.0 0.007 -0.065 0.0199 -0.066 0.003 -0.303 3.270E-02 -1.106E-02 3.265E-05 1.209E-05 3.478E-04 -2.0 0.005 0.000 -0.0032 0.000 0.005 18.814 3.270E-02 -1.214E-02 0.000E+00 0.000E+00 0.000E+00 0.0 0.007 0.065 -0.0286 0.065 0.007 -0.438 3.270E-02 -1.314E-02 3.265E-05 1.320E-05 -3.478E-04 2.0 0.014 0.131 -0.0558 0.131 0.009 -0.425 3.270E-02 -1.380E-02 1.306E-04 5.237E-05 -6.956E-04 4.0 0.025 0.196 -0.0839 0.197 0.011 -0.425 3.357E-02 -1.428E-02 2.965E-04 1.178E-04 -1.044E-03 8.0 0.061 0.337 -0.1429 0.343 0.014 -0.417 3.744E-02 -1.421E-02 8.869E-04 3.466E-04 -1.794E-03 12.0 0.122 0.496 -0.1976 0.510 0.017 -0.387 3.986E-02 -1.540E-02 1.928E-03 7.343E-04 -2.637E-03 16.0 0.207 0.656 -0.2661 0.688 0.019 -0.387 3.906E-02 -1.782E-02 3.393E-03 1.286E-03 -3.490E-03 20.0 0.315 0.808 -0.3401 0.867 0.020 -0.392 3.666E-02 -2.019E-02 5.176E-03 1.958E-03 -4.299E-03 24.0 0.445 0.949 -0.4276 1.048 0.020 -0.408 3.395E-02 -2.357E-02 7.192E-03 2.729E-03 -5.050E-03 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING ALONE CONFIGURATION EXPOSED DOUBLE DELTA WING SOLUTION, EXAMPLE PROBLEM 2, CASE 3 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 90000.00 590.50 3.6777E+01 403.136 1.0235E+05 8.850 2.460 4.280 4.140 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -6.0 0.018 -0.131 0.0410 -0.132 0.005 -0.311 2.448E-02 -9.096E-03 1.306E-04 4.860E-05 6.956E-04 -4.0 0.012 -0.065 0.0199 -0.066 0.007 -0.301 3.270E-02 -1.106E-02 3.265E-05 1.208E-05 3.478E-04 -2.0 0.010 0.000 -0.0032 0.000 0.010 9.597 3.270E-02 -1.214E-02 0.000E+00 0.000E+00 0.000E+00 0.0 0.012 0.065 -0.0286 0.065 0.012 -0.438 3.270E-02 -1.314E-02 3.265E-05 1.320E-05 -3.478E-04 2.0 0.018 0.131 -0.0558 0.131 0.014 -0.425 3.270E-02 -1.380E-02 1.306E-04 5.235E-05 -6.956E-04 4.0 0.029 0.196 -0.0839 0.198 0.016 -0.424 3.357E-02 -1.428E-02 2.965E-04 1.177E-04 -1.044E-03 8.0 0.066 0.337 -0.1429 0.343 0.019 -0.416 3.744E-02 -1.421E-02 8.869E-04 3.464E-04 -1.794E-03 12.0 0.127 0.496 -0.1976 0.511 0.021 -0.386 3.986E-02 -1.540E-02 1.928E-03 7.340E-04 -2.637E-03 16.0 0.212 0.656 -0.2661 0.689 0.023 -0.386 3.906E-02 -1.782E-02 3.393E-03 1.286E-03 -3.490E-03 20.0 0.320 0.808 -0.3401 0.869 0.024 -0.391 3.666E-02 -2.019E-02 5.176E-03 1.957E-03 -4.299E-03 24.0 0.450 0.949 -0.4276 1.050 0.025 -0.407 3.395E-02 -2.357E-02 7.192E-03 2.728E-03 -5.050E-03 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING ALONE CONFIGURATION EXPOSED DOUBLE DELTA WING SOLUTION, EXAMPLE PROBLEM 2, CASE 3 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 2.500 0.00 2790.81 2.1162E+03 518.670 1.7671E+07 8.850 2.460 4.280 4.140 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -6.0 0.011 NDM 0.0365 NDM 0.011 -0.491 1.859E-02 -9.124E-03 NDM NDM NDM -4.0 -2.0 0.0 2.0 4.0 8.0 12.0 16.0 20.0 24.0 0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST 0** CD0= 1.050E-02 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING ALONE CONFIGURATION EXPOSED DOUBLE DELTA WING SOLUTION, EXAMPLE PROBLEM 2, CASE 3 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 2.500 90000.00 2460.43 3.6777E+01 403.136 4.2644E+05 8.850 2.460 4.280 4.140 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -6.0 0.012 NDM 0.0365 NDM 0.012 -0.491 1.859E-02 -9.124E-03 NDM NDM NDM -4.0 -2.0 0.0 2.0 4.0 8.0 12.0 16.0 20.0 24.0 0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST 0** CD0= 1.243E-02 1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE. 0 BUILD $FLTCON NMACH=2.0,MACH(1)=.60,.80,NALPHA=9.0,ALSCHD(1)=-2.0,0.0,2.0, 4.0,8.0,12.0,16.0,20.0,24.0,RNNUB(1)=2.28E6,3.04E6$ $FLTCON NMACH=3.0,MACH(1)=0.60,0.80,1.5,RNNUB(1)=4.26E6,6.4E6, 9.96E6,$ $OPTINS SREF=2.25,CBARR=0.822,BLREF=3.00$ $SYNTHS XCG=2.60,ZCG=0.0,XW=1.70,ZW=0.0,ALIW=0.0,XH=3.93, ZH=0.0,ALIH=0.0,XV=3.34,VERTUP=.TRUE.$ $BODY NX=10.0,BNOSE=2.0,BTAIL=1.0,BLN=1.46,BLA=1.97, X(1)=0.0,.175,.322,.530,.850,1.460,2.50,3.43,3.97,4.57, S(1)=0.0,.00547,.0220,.0491,.0872,.136,.136,.136,.0993,.0598, P(1)=0.0,.262,.523,.785,1.04,1.305,1.305,1.305,1.12,.866, R(1)=0.0,.0417,.0833,.125,.1665,.208,.208,.208,.178,.138$ $WGPLNF CHRDTP=0.346,SSPNE=1.29,SSPN=1.50,CHRDR=1.16,SAVSI=45.0,CHSTAT=0.25, TWISTA=0.0,SSPNDD=0.0,DHDADI=0.0,DHDADO=0.0,TYPE=1.0$ $WGSCHR TOVC=.060,DELTAY=1.30,XOVC=0.40,CLI=0.0,ALPHAI=0.0,CLALPA(1)=0.131, CLMAX(1)=.82,CMO=0.0,LERI=.0025,CLAMO=.105,YCM=0.0, SLOPE(1)=70.7,2.7,0.0,-2.5,-3.8,-4.0$ $VTPLNF CHRDTP=.420,SSPNE=.63,SSPN=.849,CHRDR=1.02,SAVSI=28.1, CHSTAT=.25,TWISTA=0.0,TYPE=1.0$ $VTSCHR TOVC=.09,XOVC=0.40,CLALPA(1)=2*0.141,LERI=.0075$ $WGSCHR CLMAXL=0.78$ $HTPLNF CHRDTP=.253,SSPNE=.52,SSPN=.67,CHRDR=.42,SAVSI=45.0,CHSTAT=0.25, TWISTA=0.0,SSPNDD=0.0,DHDADI=0.0,DHDADO=0.0,TYPE=1.0$ $HTSCHR TOVC=0.060,DELTAY=1.30,XOVC=0.40,CLI=0.0,ALPHAI=0.0,CLALPA(1)=.131, CLMAX(1)=0.82,CMO=0.0,LERI=.0025,CLAMO=.105,YCM=0.$ CASEID CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 SAVE NEXT CASE 0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP DATCOM BODY ALONE CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 4.2600E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.008 -0.003 -0.0099 -0.004 0.008 2.746 1.610E-03 5.050E-03 -1.610E-03 -1.384E-03 0.000E+00 0.0 0.008 0.000 0.0000 0.000 0.008 ****** 1.663E-03 4.947E-03 -1.663E-03 -1.355E-03 0.000E+00 2.0 0.008 0.003 0.0099 0.004 0.008 2.746 1.717E-03 4.844E-03 -1.717E-03 -1.327E-03 0.000E+00 4.0 0.008 0.007 0.0194 0.007 0.008 2.607 1.823E-03 4.640E-03 -1.823E-03 -1.271E-03 0.000E+00 8.0 0.010 0.015 0.0371 0.016 0.008 2.347 2.032E-03 4.238E-03 -2.032E-03 -1.161E-03 0.000E+00 12.0 0.013 0.023 0.0533 0.025 0.008 2.110 2.234E-03 3.852E-03 -2.234E-03 -1.055E-03 0.000E+00 16.0 0.017 0.032 0.0679 0.036 0.007 1.896 2.423E-03 3.488E-03 -2.423E-03 -9.556E-04 0.000E+00 20.0 0.022 0.043 0.0812 0.048 0.007 1.705 2.602E-03 3.143E-03 -2.602E-03 -8.613E-04 0.000E+00 24.0 0.030 0.053 0.0931 0.061 0.005 1.534 2.778E-03 2.806E-03 -2.778E-03 -7.689E-04 0.000E+00 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING ALONE CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 4.2600E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.008 -0.093 0.0150 -0.094 0.005 -0.161 4.643E-02 -7.732E-03 7.482E-06 1.178E-05 4.450E-04 0.0 0.006 0.000 0.0000 0.000 0.006 ****** 4.664E-02 -7.744E-03 0.000E+00 0.000E+00 0.000E+00 2.0 0.008 0.093 -0.0159 0.094 0.005 -0.171 4.672E-02 -8.358E-03 7.482E-06 1.180E-05 -4.450E-04 4.0 0.015 0.187 -0.0334 0.187 0.002 -0.178 4.661E-02 -9.097E-03 3.013E-05 4.744E-05 -8.915E-04 8.0 0.039 0.372 -0.0727 0.374 -0.013 -0.194 4.519E-02 -9.536E-03 1.200E-04 1.884E-04 -1.774E-03 12.0 0.078 0.548 -0.1097 0.553 -0.038 -0.199 3.824E-02 -7.841E-03 2.624E-04 4.103E-04 -2.616E-03 16.0 0.115 0.678 -0.1354 0.683 -0.076 -0.198 2.442E-02 -5.730E-03 4.073E-04 6.265E-04 -3.233E-03 20.0 0.138 0.744 -0.1556 0.746 -0.125 -0.209 7.068E-03 -3.694E-03 5.029E-04 7.562E-04 -3.548E-03 24.0 0.134 0.734 -0.1649 0.725 -0.176 -0.227 -1.181E-02 -9.999E-04 5.102E-04 7.400E-04 -3.503E-03 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP HORIZONTAL TAIL CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 4.2600E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.002 -0.016 0.0358 -0.016 0.001 -2.232 8.000E-03 -1.797E-02 2.227E-07 1.217E-06 4.193E-05 0.0 0.001 0.000 0.0000 0.000 0.001 ****** 8.000E-03 -1.786E-02 0.000E+00 0.000E+00 0.000E+00 2.0 0.002 0.016 -0.0356 0.016 0.001 -2.219 8.075E-03 -1.802E-02 2.227E-07 1.215E-06 -4.193E-05 4.0 0.003 0.032 -0.0721 0.032 0.001 -2.222 8.176E-03 -1.841E-02 9.122E-07 4.952E-06 -8.463E-05 8.0 0.009 0.065 -0.1471 0.066 0.000 -2.233 7.953E-03 -1.820E-02 3.758E-06 2.023E-05 -1.709E-04 12.0 0.018 0.096 -0.2177 0.098 -0.002 -2.230 6.713E-03 -1.580E-02 8.279E-06 4.373E-05 -2.514E-04 16.0 0.027 0.119 -0.2735 0.122 -0.006 -2.244 4.508E-03 -1.162E-02 1.307E-05 6.736E-05 -3.116E-04 20.0 0.033 0.132 -0.3107 0.135 -0.014 -2.294 2.598E-03 -8.319E-03 1.672E-05 8.359E-05 -3.458E-04 24.0 0.037 0.140 -0.3400 0.143 -0.023 -2.382 1.263E-03 -6.345E-03 1.881E-05 9.487E-05 -3.661E-04 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP VERTICAL TAIL CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 4.2600E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.002 0.000 0.0000 0.000 NDM ****** 0.000E+00 0.000E+00 -1.440E-02 5.713E-03 -1.953E-03 0.0 -1.755E-03 2.0 -1.554E-03 4.0 -1.352E-03 8.0 -9.424E-04 12.0 -5.285E-04 16.0 -1.119E-04 20.0 3.051E-04 24.0 7.207E-04 0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING-BODY CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 4.2600E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.016 -0.125 0.0032 -0.126 0.012 -0.025 6.258E-02 -1.344E-03 -1.610E-03 -1.845E-03 5.509E-04 0.0 0.014 0.000 0.0000 0.000 0.014 ****** 6.258E-02 -1.856E-03 5.528E-12 2.0 0.016 0.125 -0.0042 0.126 0.012 -0.034 6.273E-02 -2.638E-03 -5.509E-04 4.0 0.024 0.251 -0.0106 0.252 0.006 -0.042 6.269E-02 -3.666E-03 -1.104E-03 8.0 0.067 0.500 -0.0292 0.505 -0.003 -0.058 6.082E-02 -4.557E-03 -2.201E-03 12.0 0.149 0.738 -0.0470 0.752 -0.007 -0.062 5.089E-02 -3.117E-03 -3.246E-03 16.0 0.236 0.907 -0.0542 0.937 -0.023 -0.058 3.176E-02 -1.415E-03 -3.993E-03 20.0 0.992 -0.0583 9.200E-03 -1.248E-04 -4.364E-03 24.0 0.981 -0.0552 -1.458E-02 1.706E-03 -4.317E-03 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP BODY-HORIZONTAL TAIL CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 4.2600E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.010 -0.028 0.0435 -0.028 0.009 -1.560 1.376E-02 -2.179E-02 -1.610E-03 -1.845E-03 2.573E-05 0.0 0.009 0.000 0.0000 0.000 0.009 ****** 1.376E-02 -2.166E-02 1.389E-12 2.0 0.010 0.028 -0.0432 0.028 0.009 -1.551 1.393E-02 -2.201E-02 -2.573E-05 4.0 0.012 0.056 -0.0880 0.056 0.008 -1.561 1.413E-02 -2.263E-02 -5.208E-05 8.0 0.019 0.112 -0.1802 0.114 0.003 -1.580 1.355E-02 -2.171E-02 -1.052E-04 12.0 0.031 0.164 -0.2618 0.167 -0.004 -1.568 1.144E-02 -1.748E-02 -1.534E-04 16.0 0.044 0.204 -0.3201 0.208 -0.014 -1.537 8.048E-03 -1.072E-02 -1.907E-04 20.0 0.056 0.228 -0.3475 0.234 -0.026 -1.486 5.167E-03 -5.093E-03 -2.136E-04 24.0 0.067 0.245 -0.3608 0.251 -0.039 -1.436 3.261E-03 -1.568E-03 -2.293E-04 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP BODY-VERTICAL TAIL CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 4.2600E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.010 -0.003 -0.0099 -0.004 0.009 2.703 1.610E-03 5.050E-03 -1.601E-02 4.329E-03 -1.953E-03 0.0 0.009 0.000 0.0000 0.000 0.009 ****** 1.663E-03 4.947E-03 -1.755E-03 2.0 0.010 0.003 0.0099 0.004 0.009 2.703 1.717E-03 4.844E-03 -1.554E-03 4.0 0.010 0.007 0.0194 0.008 0.009 2.568 1.823E-03 4.640E-03 -1.352E-03 8.0 0.012 0.015 0.0371 0.016 0.009 2.313 2.032E-03 4.238E-03 -9.424E-04 12.0 0.014 0.023 0.0533 0.026 0.009 2.082 2.234E-03 3.852E-03 -5.285E-04 16.0 0.018 0.032 0.0679 0.036 0.009 1.873 2.423E-03 3.488E-03 -1.119E-04 20.0 0.024 0.043 0.0812 0.048 0.008 1.685 2.602E-03 3.143E-03 3.051E-04 24.0 0.031 0.053 0.0931 0.061 0.007 1.518 2.778E-03 2.806E-03 7.207E-04 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING-BODY-HORIZONTAL TAIL CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 4.2600E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.018 -0.134 0.0228 -0.134 0.013 -0.170 6.696E-02 -1.114E-02 -1.609E-03 -1.844E-03 5.928E-04 0.0 0.016 0.000 0.0000 0.000 0.016 ****** 6.695E-02 -1.168E-02 5.528E-12 2.0 0.018 0.134 -0.0239 0.134 0.013 -0.177 6.751E-02 -1.337E-02 -5.928E-04 4.0 0.026 0.270 -0.0535 0.271 0.007 -0.197 6.801E-02 -1.565E-02 -1.189E-03 8.0 0.073 0.542 -0.1228 0.546 -0.004 -0.225 6.676E-02 -1.813E-02 -2.372E-03 12.0 0.160 0.804 -0.1985 0.820 -0.011 -0.242 5.806E-02 -1.973E-02 -3.497E-03 16.0 0.255 1.006 -0.2806 1.037 -0.032 -0.270 4.049E-02 -2.182E-02 -4.305E-03 20.0 1.128 -0.3731 1.762E-02 -1.977E-02 -4.710E-03 24.0 1.147 -0.4388 -8.122E-03 -1.307E-02 -4.683E-03 0 ALPHA Q/QINF EPSLON D(EPSLON)/D(ALPHA) 0 -2.0 0.944 -1.234 0.617 0.0 0.909 0.000 0.617 2.0 0.944 1.234 0.603 4.0 0.995 2.413 0.572 8.0 1.000 4.565 0.493 12.0 1.000 6.358 0.361 16.0 1.000 7.452 0.162 20.0 1.000 7.650 -0.065 24.0 1.000 6.929 -0.180 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING-BODY-VERTICAL TAIL CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 4.2600E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.018 -0.125 0.0032 -0.126 0.013 -0.025 6.258E-02 -1.344E-03 -1.601E-02 3.868E-03 -1.402E-03 0.0 0.016 0.000 0.0000 0.000 0.016 ****** 6.258E-02 -1.856E-03 -1.755E-03 2.0 0.018 0.125 -0.0042 0.126 0.013 -0.034 6.273E-02 -2.638E-03 -2.105E-03 4.0 0.026 0.251 -0.0106 0.252 0.008 -0.042 6.269E-02 -3.666E-03 -2.456E-03 8.0 0.069 0.500 -0.0292 0.505 -0.001 -0.058 6.082E-02 -4.557E-03 -3.144E-03 12.0 0.151 0.738 -0.0470 0.753 -0.006 -0.062 5.089E-02 -3.117E-03 -3.775E-03 16.0 0.238 0.907 -0.0542 0.938 -0.022 -0.058 3.176E-02 -1.415E-03 -4.105E-03 20.0 0.992 -0.0583 9.200E-03 -1.248E-04 -4.059E-03 24.0 0.981 -0.0552 -1.458E-02 1.706E-03 -3.596E-03 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 4.2600E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.019 -0.134 0.0228 -0.135 0.015 -0.170 6.696E-02 -1.114E-02 -1.601E-02 3.869E-03 -1.360E-03 0.0 0.017 0.000 0.0000 0.000 0.017 ****** 6.695E-02 -1.168E-02 -1.755E-03 2.0 0.019 0.134 -0.0239 0.134 0.015 -0.177 6.751E-02 -1.337E-02 -2.147E-03 4.0 0.028 0.270 -0.0535 0.271 0.009 -0.197 6.801E-02 -1.565E-02 -2.541E-03 8.0 0.074 0.542 -0.1228 0.547 -0.002 -0.225 6.676E-02 -1.813E-02 -3.315E-03 12.0 0.162 0.804 -0.1985 0.820 -0.009 -0.242 5.806E-02 -1.973E-02 -4.026E-03 16.0 0.257 1.006 -0.2806 1.038 -0.030 -0.270 4.049E-02 -2.182E-02 -4.417E-03 20.0 1.128 -0.3731 1.762E-02 -1.977E-02 -4.405E-03 24.0 1.147 -0.4388 -8.122E-03 -1.307E-02 -3.962E-03 0 ALPHA Q/QINF EPSLON D(EPSLON)/D(ALPHA) 0 -2.0 0.944 -1.234 0.617 0.0 0.909 0.000 0.617 2.0 0.944 1.234 0.603 4.0 0.995 2.413 0.572 8.0 1.000 4.565 0.493 12.0 1.000 6.358 0.361 16.0 1.000 7.452 0.162 20.0 1.000 7.650 -0.065 24.0 1.000 6.929 -0.180 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP DATCOM BODY ALONE CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.800 6.4000E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.008 NDM NDM NDM NDM 2.892 1.599E-03 4.625E-03 -1.599E-03 -1.267E-03 0.000E+00 0.0 0.008 0.000E+00 2.0 0.008 0.000E+00 4.0 0.008 0.000E+00 8.0 0.008 0.000E+00 12.0 0.009 0.000E+00 16.0 0.010 0.000E+00 20.0 0.011 0.000E+00 24.0 0.012 0.000E+00 0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING ALONE CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.800 6.4000E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.006 NDM NDM NDM NDM -0.239 5.044E-02 -1.206E-02 NDM NDM NDM 0.0 NDM 2.0 NDM 4.0 NDM 8.0 NDM 12.0 NDM 16.0 NDM 20.0 NDM 24.0 NDM 0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP HORIZONTAL TAIL CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.800 6.4000E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.001 NDM NDM NDM NDM -2.232 8.485E-03 -1.894E-02 NDM NDM NDM 0.0 NDM 2.0 NDM 4.0 NDM 8.0 NDM 12.0 NDM 16.0 NDM 20.0 NDM 24.0 NDM 0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP VERTICAL TAIL CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.800 6.4000E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.003 0.000 0.0000 0.000 NDM ****** 0.000E+00 0.000E+00 NDM NDM NDM 0.0 NDM 2.0 NDM 4.0 NDM 8.0 NDM 12.0 NDM 16.0 NDM 20.0 NDM 24.0 NDM 0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING-BODY CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.800 6.4000E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.017 -0.130 0.0077 -0.131 0.012 -0.059 6.513E-02 -7.869E-03 -1.599E-03 -1.941E-03 9.441E-04 0.0 0.013 0.000 0.000 0.013 6.513E-02 0.000E+00 2.0 0.017 0.130 0.131 0.012 6.513E-02 -9.441E-04 4.0 0.026 0.261 0.262 0.008 6.513E-02 -1.888E-03 8.0 0.082 0.521 0.527 0.009 6.513E-02 -3.776E-03 12.0 0.158 0.782 0.797 -0.008 6.513E-02 -5.664E-03 16.0 0.246 1.042 1.070 -0.050 6.513E-02 -7.553E-03 20.0 1.303 6.513E-02 -9.441E-03 24.0 1.563 6.513E-02 -1.133E-02 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP BODY-HORIZONTAL TAIL CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.800 6.4000E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.009 -0.027 NDM -0.027 0.008 -1.623 1.342E-02 -2.178E-02 -1.599E-03 -1.941E-03 6.755E-05 0.0 0.000 1.342E-02 0.000E+00 2.0 0.027 1.342E-02 -6.755E-05 4.0 0.054 1.342E-02 -1.351E-04 8.0 0.107 1.342E-02 -2.702E-04 12.0 0.161 1.342E-02 -4.053E-04 16.0 0.215 1.342E-02 -5.404E-04 20.0 0.268 1.342E-02 -6.755E-04 24.0 0.322 1.342E-02 -8.106E-04 0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP BODY-VERTICAL TAIL CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.800 6.4000E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.010 NDM NDM NDM NDM 2.892 1.599E-03 4.625E-03 NDM NDM NDM 0.0 0.010 NDM 2.0 0.010 NDM 4.0 0.011 NDM 8.0 0.011 NDM 12.0 0.012 NDM 16.0 0.012 NDM 20.0 0.014 NDM 24.0 0.015 NDM 0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING-BODY-HORIZONTAL TAIL CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.800 6.4000E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.014 NDM NDM NDM NDM 0.028 6.903E-02 1.943E-03 NDM NDM NDM 0.0 NDM 2.0 NDM 4.0 NDM 8.0 NDM 12.0 NDM 16.0 NDM 20.0 NDM 24.0 NDM 0 ALPHA Q/QINF EPSLON D(EPSLON)/D(ALPHA) 0 -2.0 0.914 0.000 0.639 0.0 2.0 4.0 8.0 12.0 16.0 20.0 24.0 0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING-BODY-VERTICAL TAIL CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.800 6.4000E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.020 -0.130 NDM -0.131 0.015 -0.121 6.513E-02 -7.869E-03 -1.599E-03 -1.941E-03 NDM 0.0 0.016 0.000 NDM 0.000 0.016 6.513E-02 NDM 2.0 0.020 0.130 NDM 0.131 0.015 6.513E-02 NDM 4.0 0.029 0.261 NDM 0.262 0.011 6.513E-02 NDM 8.0 0.085 0.521 NDM 0.528 0.012 6.513E-02 NDM 12.0 0.161 0.782 NDM 0.798 -0.005 6.513E-02 NDM 16.0 0.249 1.042 NDM 1.070 -0.048 6.513E-02 NDM 20.0 1.303 NDM 6.513E-02 NDM 24.0 1.563 NDM 6.513E-02 NDM 0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.800 6.4000E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.017 NDM NDM NDM NDM 0.028 6.903E-02 1.943E-03 NDM NDM NDM 0.0 NDM 2.0 NDM 4.0 NDM 8.0 NDM 12.0 NDM 16.0 NDM 20.0 NDM 24.0 NDM 0 ALPHA Q/QINF EPSLON D(EPSLON)/D(ALPHA) 0 -2.0 0.914 0.000 0.639 0.0 2.0 4.0 8.0 12.0 16.0 20.0 24.0 0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CONFIGURATION AUXILIARY AND PARTIAL OUTPUT WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.800 6.4000E+06 2.250 0.822 3.000 2.600 0.000 BASIC BODY PROPERTIES WETTED AREA XCG ZCG BASE AREA ZERO LIFT DRAG BASE DRAG FRICTION DRAG PRESSURE DRAG 0.5035E+01 2.60 0.00 0.0598 0.7576E-02 0.1690E-02 0.5487E-02 0.3992E-03 XCG RELATIVE TO THEORETICAL LEADING EDGE MAC= 0.20 BASIC PLANFORM PROPERTIES TAPER ASPECT QUARTER CHORD QUARTER CHORD ZERO LIFT FRICTION AREA RATIO RATIO SWEEP MAC X(MAC) Y(MAC) DRAG COEFFICIENT 0 WING TOTAL THEORITICAL + 0.2259E+01 0.298 0.3984E+01 45.000 0.826E+00 0.260E+01 0.615E+00 TOTAL EXPOSED + 0.1796E+01 0.331 0.3707E+01 45.000 0.755E+00 0.274E+01 0.747E+00 0.573E-02 0.335E-02 0 HORIZONTAL TAIL TOTAL THEORITICAL + 0.4509E+00 0.602 0.3982E+01 45.000 0.343E+00 0.434E+01 0.307E+00 TOTAL EXPOSED + 0.3305E+00 0.661 0.3272E+01 45.000 0.322E+00 0.443E+01 0.392E+00 0.123E-02 0.391E-02 0 VERTICAL TAIL TOTAL THEORITICAL + 0.6113E+00 0.412 0.1179E+01 28.100 0.762E+00 0.379E+01 0.366E+00 TOTAL EXPOSED + 0.4048E+00 0.485 0.9804E+00 28.100 0.668E+00 0.386E+01 0.498E+00 NA NA 0*** NA PRINTED WHEN METHOD NOT APPLICABLE 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CONFIGURATION AUXILIARY AND PARTIAL OUTPUT WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.800 6.4000E+06 2.250 0.822 3.000 2.600 0.000 0 CLA-B(W)= 7.443E-03 CLA-W(B)= 5.609E-02 K-B(W)= 1.476E-01 K-W(B)= 1.112E+00 XAC/C-B(W)= 6.820E-01 0 CLA-B(H)= 1.777E-03 CLA-H(B)= 1.005E-02 K-B(H)= 2.094E-01 K-H(B)= 1.184E+00 XAC/C-B(H)= 4.272E-01 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CONFIGURATION AUXILIARY AND PARTIAL OUTPUT WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.800 6.4000E+06 2.250 0.822 3.000 2.600 0.000 *** WING DATA FAIRING *** CDL/CL**2 = 0.1977E+00 CLB/CL =-0.5165E-02 FORCE BREAK MACH NUMBER (ZERO SWEEP) = 0.9321E+00 FORCE BREAK MACH NUMBER (WITH SWEEP) = 0.9552E+00 MACH(A) = 1.025 CLA(A) = 0.5384E-01 MACH(B) = 1.095 CLA(B) = 0.4967E-01 (CLB/CL)M=0.6 =-0.4771E-02 (CLB/CL)M=1.4 =-0.2642E-02 LIFT-CURVE-SLOPE INTERPOLATION TABLE MACH CL-ALPHA 0.750 0.4868E-01 0.955 0.5710E-01 1.025 0.5384E-01 1.095 0.4967E-01 1.400 0.4200E-01 *** WING-BODY DATA FAIRING *** CLB/CL =-0.7247E-02 (CLB/CL)MFB =-0.4718E-02 (CLB/CL)M=1.4 =-0.2043E-02 (CNA)M=1.4 = 0.5406E-01 *** HORIZONTAL TAIL DATA FAIRING *** CDL/CL**2 = 0.2357E+00 CLB/CL =-0.2349E-02 FORCE BREAK MACH NUMBER (ZERO SWEEP) = 0.9738E+00 FORCE BREAK MACH NUMBER (WITH SWEEP) = 0.9838E+00 MACH(A) = 1.054 CLA(A) = 0.9185E-02 MACH(B) = 1.124 CLA(B) = 0.8436E-02 (CLB/CL)M=0.6 =-0.2620E-02 (CLB/CL)M=1.4 =-0.2496E-03 LIFT-CURVE-SLOPE INTERPOLATION TABLE MACH CL-ALPHA 0.750 0.8234E-02 0.984 0.9696E-02 1.054 0.9185E-02 1.124 0.8436E-02 1.400 0.7109E-02 *** HORIZONTAL TAIL-BODY DATA FAIRING *** CLB/CL =-0.2516E-02 (CLB/CL)MFB =-0.9533E-03 (CLB/CL)M=1.4 =-0.1640E-03 (CNA)M=1.4 = 0.1058E-01 *** BODY-WING-HORIZONTAL TAIL DATA FAIRING *** DRAG DIVERGENCE MACH NUMBER = 0.931 MACH CDO 0.600 0.1702E-01 0.700 0.1701E-01 1.100 0.2431E-01 1.400 0.2415E-01 1 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP DATCOM BODY ALONE CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 1.500 9.9600E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.014 -0.004 -0.0085 -0.004 0.014 1.960 1.916E-03 4.242E-03 -1.916E-03 -1.162E-03 0.000E+00 0.0 0.014 0.000 0.0000 0.000 0.014 ****** 1.916E-03 4.242E-03 -1.916E-03 -1.162E-03 0.000E+00 2.0 0.014 0.004 0.0085 0.004 0.014 1.960 2.429E-03 4.326E-03 -2.429E-03 -1.185E-03 0.000E+00 4.0 0.015 0.010 0.0173 0.011 0.014 1.614 3.430E-03 4.479E-03 -3.430E-03 -1.227E-03 0.000E+00 8.0 0.018 0.027 0.0358 0.030 0.014 1.210 5.371E-03 4.720E-03 -5.371E-03 -1.293E-03 0.000E+00 12.0 0.025 0.053 0.0551 0.057 0.014 0.971 7.439E-03 4.934E-03 -7.439E-03 -1.352E-03 0.000E+00 16.0 0.038 0.087 0.0752 0.094 0.013 0.800 9.918E-03 5.192E-03 -9.918E-03 -1.423E-03 0.000E+00 20.0 0.061 0.132 0.0966 0.145 0.012 0.666 1.294E-02 5.552E-03 -1.294E-02 -1.521E-03 0.000E+00 24.0 0.098 0.190 0.1197 0.214 0.012 0.560 1.623E-02 5.973E-03 -1.623E-02 -1.637E-03 0.000E+00 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING ALONE CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 1.500 9.9600E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.008 -0.077 0.0298 -0.077 0.005 -0.386 3.832E-02 -1.492E-02 NDM NDM 1.758E-04 0.0 0.006 0.000 0.0000 0.000 0.006 ****** 3.856E-02 0.000E+00 2.0 0.008 0.077 -0.0298 0.077 0.005 -0.386 3.867E-02 -1.758E-04 4.0 0.015 0.155 -0.0597 0.155 0.004 -0.384 3.859E-02 -3.530E-04 8.0 0.041 0.308 -0.1193 0.310 -0.002 -0.385 3.719E-02 -7.054E-04 12.0 0.082 0.452 NDM 0.459 -0.014 3.437E-02 -1.044E-03 16.0 0.133 0.583 NDM 0.597 -0.033 3.018E-02 -1.356E-03 20.0 0.186 0.694 NDM 0.715 -0.063 2.484E-02 -1.626E-03 24.0 0.234 0.781 NDM 0.809 -0.104 1.898E-02 -1.839E-03 0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP HORIZONTAL TAIL CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 1.500 9.9600E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.002 -0.014 0.0308 -0.014 0.001 -2.269 6.699E-03 -1.539E-02 NDM NDM 3.023E-06 0.0 0.001 0.000 0.0000 0.000 0.001 ****** 6.757E-03 0.000E+00 2.0 0.002 0.014 -0.0308 0.014 0.001 -2.269 6.787E-03 -3.023E-06 4.0 0.003 0.027 -0.0615 0.027 0.001 -2.257 6.789E-03 -6.080E-06 8.0 0.007 0.054 -0.1231 0.055 0.000 -2.255 6.568E-03 -1.217E-05 12.0 0.014 0.080 NDM 0.081 -0.002 6.094E-03 -1.805E-05 16.0 0.023 0.103 NDM 0.105 -0.006 5.396E-03 -2.347E-05 20.0 0.033 0.123 NDM 0.127 -0.011 4.516E-03 -2.824E-05 24.0 0.042 0.139 NDM 0.144 -0.019 3.536E-03 -3.207E-05 0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP VERTICAL TAIL CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 1.500 9.9600E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.003 0.000 0.0000 0.000 0.003 ****** 0.000E+00 0.000E+00 -1.162E-02 5.531E-03 -2.120E-03 0.0 -1.928E-03 2.0 -1.734E-03 4.0 -1.537E-03 8.0 -1.139E-03 12.0 -7.356E-04 16.0 -3.285E-04 20.0 8.025E-05 24.0 4.886E-04 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING-BODY CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 1.500 9.9600E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.022 -0.100 -0.0180 -0.101 0.019 0.178 4.961E-02 -1.384E-02 -1.643E-03 -2.045E-03 1.758E-04 0.0 0.020 0.000 0.0000 0.000 0.020 ****** 5.019E-02 0.000E+00 2.0 0.022 0.100 -0.0265 0.101 0.019 -0.262 5.083E-02 -1.758E-04 4.0 0.029 0.203 -0.0530 0.205 0.015 -0.259 5.173E-02 -3.530E-04 8.0 0.059 0.412 -0.1047 0.416 0.001 -0.251 5.174E-02 -7.054E-04 12.0 0.107 0.617 -0.1528 0.626 -0.024 -0.244 4.940E-02 -1.044E-03 16.0 0.171 0.808 -0.1947 0.823 -0.058 -0.236 4.558E-02 -1.356E-03 20.0 0.247 0.982 -0.2270 1.007 -0.104 -0.225 4.185E-02 -1.626E-03 24.0 0.332 1.142 -0.2463 1.178 -0.162 -0.209 3.839E-02 -1.839E-03 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP BODY-HORIZONTAL TAIL CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 1.500 9.9600E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.016 -0.021 0.0421 -0.021 0.015 -1.972 1.005E-02 -1.587E-02 -1.643E-03 -2.045E-03 3.023E-06 0.0 0.015 0.000 0.0000 0.000 0.015 ****** 1.040E-02 0.000E+00 2.0 0.016 0.021 -0.0421 0.021 0.015 -1.972 1.094E-02 -3.023E-06 4.0 0.017 0.044 -0.0843 0.045 0.014 -1.879 1.190E-02 -6.080E-06 8.0 0.025 0.095 -0.1677 0.097 0.012 -1.725 1.318E-02 -1.217E-05 12.0 0.039 0.149 -0.2451 0.154 0.008 -1.590 1.429E-02 -1.805E-05 16.0 0.062 0.209 -0.3080 0.218 0.002 -1.414 1.569E-02 -2.347E-05 20.0 0.094 0.275 -0.3557 0.290 -0.006 -1.225 1.746E-02 -2.824E-05 24.0 0.139 0.349 -0.3887 0.375 -0.015 -1.036 1.947E-02 -3.207E-05 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP BODY-VERTICAL TAIL CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 1.500 9.9600E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.017 -0.004 -0.0085 -0.004 0.014 1.960 1.916E-03 4.242E-03 -1.354E-02 4.369E-03 -2.120E-03 0.0 0.017 0.000 0.0000 0.000 0.014 ****** 1.916E-03 4.242E-03 -1.928E-03 2.0 0.017 0.004 0.0085 0.004 0.014 1.960 2.429E-03 4.326E-03 -1.734E-03 4.0 0.017 0.010 0.0173 0.011 0.014 1.614 3.430E-03 4.479E-03 -1.537E-03 8.0 0.021 0.027 0.0358 0.030 0.014 1.210 5.371E-03 4.720E-03 -1.139E-03 12.0 0.028 0.053 0.0551 0.057 0.014 0.971 7.439E-03 4.934E-03 -7.356E-04 16.0 0.041 0.087 0.0752 0.094 0.013 0.800 9.918E-03 5.192E-03 -3.285E-04 20.0 0.064 0.132 0.0966 0.145 0.012 0.666 1.294E-02 5.552E-03 8.025E-05 24.0 0.100 0.190 0.1197 0.214 0.012 0.560 1.623E-02 5.973E-03 4.886E-04 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING-BODY-HORIZONTAL TAIL CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 1.500 9.9600E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.024 -0.111 0.0491 -0.112 0.020 -0.440 5.481E-02 -2.457E-02 -1.643E-03 -2.045E-03 1.758E-04 0.0 0.021 0.000 0.0000 0.000 0.021 ****** 5.454E-02 -2.402E-02 0.000E+00 2.0 0.024 0.111 -0.0491 0.112 0.020 -0.440 5.480E-02 -2.455E-02 -1.758E-04 4.0 0.032 0.224 -0.0984 0.226 0.016 -0.435 5.480E-02 -2.459E-02 -3.530E-04 8.0 0.064 0.453 -0.1978 0.458 0.001 -0.432 5.479E-02 -2.473E-02 -7.054E-04 12.0 0.117 0.676 -0.3011 0.686 -0.026 -0.439 5.488E-02 -2.510E-02 -1.044E-03 16.0 0.188 0.883 -0.4105 0.901 -0.063 -0.456 5.506E-02 -2.566E-02 -1.356E-03 20.0 0.271 1.073 -0.5255 1.102 -0.112 -0.477 5.532E-02 -2.628E-02 -1.626E-03 24.0 0.365 1.248 -0.6420 1.289 -0.175 -0.498 5.559E-02 -2.675E-02 -1.839E-03 0 ALPHA Q/QINF EPSLON D(EPSLON)/D(ALPHA) 0 -2.0 0.964 -0.717 0.358 0.0 0.915 0.000 0.358 2.0 0.964 0.717 0.359 4.0 0.963 1.437 0.359 8.0 0.943 2.858 0.346 12.0 0.921 4.202 0.319 16.0 0.901 5.413 0.280 20.0 0.884 6.445 0.231 24.0 0.865 7.259 0.176 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING-BODY-VERTICAL TAIL CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 1.500 9.9600E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.025 -0.100 -0.0180 -0.101 0.021 0.178 4.961E-02 -1.384E-02 -1.325E-02 3.481E-03 -1.942E-03 0.0 0.022 0.000 0.0000 0.000 0.022 ****** 5.019E-02 -1.926E-03 2.0 0.025 0.100 -0.0265 0.101 0.021 -0.262 5.083E-02 -1.908E-03 4.0 0.032 0.203 -0.0530 0.205 0.018 -0.258 5.173E-02 -1.889E-03 8.0 0.061 0.412 -0.1047 0.417 0.003 -0.251 5.174E-02 -1.844E-03 12.0 0.110 0.617 -0.1528 0.627 -0.021 -0.244 4.940E-02 -1.779E-03 16.0 0.174 0.808 -0.1947 0.824 -0.056 -0.236 4.558E-02 -1.684E-03 20.0 0.250 0.982 -0.2270 1.008 -0.101 -0.225 4.185E-02 -1.546E-03 24.0 0.334 1.142 -0.2463 1.180 -0.159 -0.209 3.839E-02 -1.351E-03 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION CONFIGURATION BUILDUP, EXAMPLE PROBLEM 3, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 1.500 9.9600E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.026 -0.111 0.0491 -0.112 0.022 -0.440 5.481E-02 -2.457E-02 -1.326E-02 3.486E-03 -1.944E-03 0.0 0.023 0.000 0.0000 0.000 0.023 ****** 5.454E-02 -2.402E-02 -1.928E-03 2.0 0.026 0.111 -0.0491 0.112 0.022 -0.440 5.480E-02 -2.455E-02 -1.909E-03 4.0 0.034 0.224 -0.0984 0.226 0.018 -0.435 5.480E-02 -2.459E-02 -1.890E-03 8.0 0.067 0.453 -0.1978 0.458 0.003 -0.432 5.479E-02 -2.473E-02 -1.845E-03 12.0 0.120 0.676 -0.3011 0.686 -0.023 -0.439 5.488E-02 -2.510E-02 -1.780E-03 16.0 0.190 0.883 -0.4105 0.902 -0.060 -0.455 5.506E-02 -2.566E-02 -1.685E-03 20.0 0.274 1.073 -0.5255 1.102 -0.110 -0.477 5.532E-02 -2.628E-02 -1.546E-03 24.0 0.367 1.248 -0.6420 1.290 -0.172 -0.498 5.559E-02 -2.675E-02 -1.350E-03 0 ALPHA Q/QINF EPSLON D(EPSLON)/D(ALPHA) 0 -2.0 0.964 -0.717 0.358 0.0 0.915 0.000 0.358 2.0 0.964 0.717 0.359 4.0 0.963 1.437 0.359 8.0 0.943 2.858 0.346 12.0 0.921 4.202 0.319 16.0 0.901 5.413 0.280 20.0 0.884 6.445 0.231 24.0 0.865 7.259 0.176 1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE. 0 $EXPR01 CLAWB(1)=.0575,CMAWB(1)=-.0050, CDWB(1)=.015,.014,.015,.019,.064,.141,.216,.302,.410, CLWB(1)=-.115,0.0,.115,.23,.47,.65,.76,.81,.90, CMWB(1)=.010,0.0,-.010,-.020,-.038,-.002,-.013,-.013,-.020, CLAB(1)=.002,CMAB(1)=.0039, CDB(1)=.012,.010,.012,.013,.014,.016,.020,.030,.047, CLB(1)=-.004,0.0,.004,.008,.012,.020,.060,.085,.10, CMB(1)=-.0078,.0078,.020,.038,.060,.083,.110,.140,.165,$ $EXPR02 CLAWB(1)=.06,CLAB(1)=.002,CMAB(1)=.0039, ALPOW=0.0,ALPLW=8.8,ACLMW=12.01,CLMW=1.39, ALPOH=0.0,ALPLH=6.2,ACLMH=10.10,CLMH=1.02,$ CASEID INCLUDES BODY AND WING-BODY EXPERIMENTAL DATA, EXAMPLE PROBLEM 3, CASE 2 SAVE NEXT CASE 0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION INCLUDES BODY AND WING-BODY EXPERIMENTAL DATA, EXAMPLE PROBLEM 3, CASE 2 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 4.2600E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.018 -0.124 0.0296 -0.124 0.014 -0.238 6.188E-02 -1.480E-02 -1.640E-02 3.869E-03 -1.405E-03 0.0 0.017 0.000 0.0000 0.000 0.017 ****** 6.187E-02 -1.482E-02 -1.755E-03 2.0 0.018 0.124 -0.0296 0.124 0.014 -0.238 6.228E-02 -1.573E-02 -2.102E-03 4.0 0.023 0.249 -0.0629 0.250 0.005 -0.252 6.365E-02 -1.682E-02 -2.449E-03 8.0 0.071 0.511 -0.1315 0.516 -0.001 -0.255 5.844E-02 -1.132E-02 -3.182E-03 12.0 0.153 0.717 -0.1535 0.733 0.001 -0.209 4.342E-02 -1.349E-02 -3.641E-03 16.0 0.237 0.859 -0.2394 0.891 -0.009 -0.269 2.873E-02 -2.178E-02 -3.769E-03 20.0 0.336 0.946 -0.3278 1.004 -0.008 -0.326 2.592E-02 -2.052E-02 -3.606E-03 24.0 0.455 1.066 -0.4036 1.159 -0.018 -0.348 3.396E-02 -1.740E-02 -3.607E-03 0 ALPHA Q/QINF EPSLON D(EPSLON)/D(ALPHA) 0 -2.0 0.944 -1.234 0.617 0.0 0.909 0.000 0.617 2.0 0.944 1.234 0.603 4.0 0.995 2.413 0.572 8.0 1.000 4.565 0.493 12.0 1.000 6.358 0.361 16.0 1.000 7.452 0.162 20.0 1.000 7.650 -0.065 24.0 1.000 6.929 -0.180 0*NOTE* OUTPUT REFLECTS EXPERIMENTAL DATA INPUTS 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION INCLUDES BODY AND WING-BODY EXPERIMENTAL DATA, EXAMPLE PROBLEM 3, CASE 2 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.800 6.4000E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.021 -0.153 NDM -0.153 0.016 0.038 6.390E-02 2.441E-03 NDM NDM NDM 0.0 NDM 2.0 NDM 4.0 NDM 8.0 NDM 12.0 NDM 16.0 NDM 20.0 NDM 24.0 NDM 0 ALPHA Q/QINF EPSLON D(EPSLON)/D(ALPHA) 0 -2.0 0.914 0.000 0.639 0.0 2.0 4.0 8.0 12.0 16.0 20.0 24.0 0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST 0*NOTE* OUTPUT REFLECTS EXPERIMENTAL DATA INPUTS 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CONFIGURATION AUXILIARY AND PARTIAL OUTPUT WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION INCLUDES BODY AND WING-BODY EXPERIMENTAL DATA, EXAMPLE PROBLEM 3, CASE 2 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.800 6.4000E+06 2.250 0.822 3.000 2.600 0.000 BASIC BODY PROPERTIES WETTED AREA XCG ZCG BASE AREA ZERO LIFT DRAG BASE DRAG FRICTION DRAG PRESSURE DRAG 0.5035E+01 2.60 0.00 0.0598 0.7576E-02 0.1690E-02 0.5487E-02 0.3992E-03 XCG RELATIVE TO THEORETICAL LEADING EDGE MAC= 0.20 BASIC PLANFORM PROPERTIES TAPER ASPECT QUARTER CHORD QUARTER CHORD ZERO LIFT FRICTION AREA RATIO RATIO SWEEP MAC X(MAC) Y(MAC) DRAG COEFFICIENT 0 WING TOTAL THEORITICAL + 0.2259E+01 0.298 0.3984E+01 45.000 0.826E+00 0.260E+01 0.615E+00 TOTAL EXPOSED + 0.1796E+01 0.331 0.3707E+01 45.000 0.755E+00 0.274E+01 0.747E+00 0.774E-02 0.335E-02 0 HORIZONTAL TAIL TOTAL THEORITICAL + 0.4509E+00 0.602 0.3982E+01 45.000 0.343E+00 0.434E+01 0.307E+00 TOTAL EXPOSED + 0.3305E+00 0.661 0.3272E+01 45.000 0.322E+00 0.443E+01 0.392E+00 0.130E-02 0.391E-02 0 VERTICAL TAIL TOTAL THEORITICAL + 0.6113E+00 0.412 0.1179E+01 28.100 0.762E+00 0.379E+01 0.366E+00 TOTAL EXPOSED + 0.4048E+00 0.485 0.9804E+00 28.100 0.668E+00 0.386E+01 0.498E+00 NA NA 0*** NA PRINTED WHEN METHOD NOT APPLICABLE 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CONFIGURATION AUXILIARY AND PARTIAL OUTPUT WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION INCLUDES BODY AND WING-BODY EXPERIMENTAL DATA, EXAMPLE PROBLEM 3, CASE 2 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.800 6.4000E+06 2.250 0.822 3.000 2.600 0.000 0 CLA-B(W)= 7.443E-03 CLA-W(B)= 5.609E-02 K-B(W)= 1.476E-01 K-W(B)= 1.112E+00 XAC/C-B(W)= 6.820E-01 0 CLA-B(H)= 1.777E-03 CLA-H(B)= 1.005E-02 K-B(H)= 2.094E-01 K-H(B)= 1.184E+00 XAC/C-B(H)= 4.272E-01 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CONFIGURATION AUXILIARY AND PARTIAL OUTPUT WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION INCLUDES BODY AND WING-BODY EXPERIMENTAL DATA, EXAMPLE PROBLEM 3, CASE 2 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.800 6.4000E+06 2.250 0.822 3.000 2.600 0.000 *** WING DATA FAIRING *** CDL/CL**2 = 0.1977E+00 CLB/CL =-0.5165E-02 FORCE BREAK MACH NUMBER (ZERO SWEEP) = 0.9321E+00 FORCE BREAK MACH NUMBER (WITH SWEEP) = 0.9552E+00 MACH(A) = 1.025 CLA(A) = 0.5384E-01 MACH(B) = 1.095 CLA(B) = 0.4967E-01 (CLB/CL)M=0.6 =-0.4771E-02 (CLB/CL)M=1.4 =-0.2642E-02 LIFT-CURVE-SLOPE INTERPOLATION TABLE MACH CL-ALPHA 0.750 0.4868E-01 0.955 0.5710E-01 1.025 0.5384E-01 1.095 0.4967E-01 1.400 0.4200E-01 *** WING-BODY DATA FAIRING *** CLB/CL =-0.6150E-02 (CLB/CL)MFB =-0.4718E-02 (CLB/CL)M=1.4 =-0.2043E-02 (CNA)M=1.4 = 0.5406E-01 *** HORIZONTAL TAIL DATA FAIRING *** CDL/CL**2 = 0.2357E+00 CLB/CL =-0.2349E-02 FORCE BREAK MACH NUMBER (ZERO SWEEP) = 0.9738E+00 FORCE BREAK MACH NUMBER (WITH SWEEP) = 0.9838E+00 MACH(A) = 1.054 CLA(A) = 0.9185E-02 MACH(B) = 1.124 CLA(B) = 0.8436E-02 (CLB/CL)M=0.6 =-0.2620E-02 (CLB/CL)M=1.4 =-0.2496E-03 LIFT-CURVE-SLOPE INTERPOLATION TABLE MACH CL-ALPHA 0.750 0.8234E-02 0.984 0.9696E-02 1.054 0.9185E-02 1.124 0.8436E-02 1.400 0.7109E-02 *** HORIZONTAL TAIL-BODY DATA FAIRING *** CLB/CL =-0.2669E-02 (CLB/CL)MFB =-0.9533E-03 (CLB/CL)M=1.4 =-0.1640E-03 (CNA)M=1.4 = 0.1058E-01 *** BODY-WING-HORIZONTAL TAIL DATA FAIRING *** DRAG DIVERGENCE MACH NUMBER = 0.931 MACH CDO 0.600 0.1702E-01 0.700 0.1701E-01 1.100 0.2431E-01 1.400 0.2415E-01 1 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION INCLUDES BODY AND WING-BODY EXPERIMENTAL DATA, EXAMPLE PROBLEM 3, CASE 2 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 1.500 9.9600E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.026 -0.111 0.0491 -0.112 0.022 -0.440 5.481E-02 -2.457E-02 -1.326E-02 3.486E-03 -1.944E-03 0.0 0.023 0.000 0.0000 0.000 0.023 ****** 5.454E-02 -2.402E-02 -1.928E-03 2.0 0.026 0.111 -0.0491 0.112 0.022 -0.440 5.480E-02 -2.455E-02 -1.909E-03 4.0 0.034 0.224 -0.0984 0.226 0.018 -0.435 5.480E-02 -2.459E-02 -1.890E-03 8.0 0.067 0.453 -0.1978 0.458 0.003 -0.432 5.479E-02 -2.473E-02 -1.845E-03 12.0 0.120 0.676 -0.3011 0.686 -0.023 -0.439 5.488E-02 -2.510E-02 -1.780E-03 16.0 0.190 0.883 -0.4105 0.902 -0.060 -0.455 5.506E-02 -2.566E-02 -1.685E-03 20.0 0.274 1.073 -0.5255 1.102 -0.110 -0.477 5.532E-02 -2.628E-02 -1.546E-03 24.0 0.367 1.248 -0.6420 1.290 -0.172 -0.498 5.559E-02 -2.675E-02 -1.350E-03 0 ALPHA Q/QINF EPSLON D(EPSLON)/D(ALPHA) 0 -2.0 0.964 -0.717 0.358 0.0 0.915 0.000 0.358 2.0 0.964 0.717 0.359 4.0 0.963 1.437 0.359 8.0 0.943 2.858 0.346 12.0 0.921 4.202 0.319 16.0 0.901 5.413 0.280 20.0 0.884 6.445 0.231 24.0 0.865 7.259 0.176 1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE. 0 $TVTPAN BVP=0.40,BV=.60,BDV=.36,BH=1.10,SV=.360,VPHITE=20.0,VLP=1.04,ZP=0.0$ CASEID INCLUDES BODY AND WING-BODY EXPERIMENTAL DATA, EXAMPLE PROBLEM 3, CASE 3 SAVE NEXT CASE 0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING-BODY-HORIZONTAL TAIL-VERTICAL TAIL-TWIN VERTICAL PANEL CONFIGURATION INCLUDES BODY AND WING-BODY EXPERIMENTAL DATA, EXAMPLE PROBLEM 3, CASE 3 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 4.2600E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.018 -0.124 0.0296 -0.124 0.014 -0.238 6.188E-02 -1.480E-02 -2.237E-02 5.940E-03 -1.477E-03 0.0 0.017 0.000 0.0000 0.000 0.017 ****** 6.187E-02 -1.482E-02 -1.755E-03 2.0 0.018 0.124 -0.0296 0.124 0.014 -0.238 6.228E-02 -1.573E-02 -2.030E-03 4.0 0.023 0.249 -0.0629 0.250 0.005 -0.252 6.365E-02 -1.682E-02 -2.304E-03 8.0 0.071 0.511 -0.1315 0.516 -0.001 -0.255 5.844E-02 -1.132E-02 -2.894E-03 12.0 0.153 0.717 -0.1535 0.733 0.001 -0.209 4.342E-02 -1.349E-02 -3.210E-03 16.0 0.237 0.859 -0.2394 0.891 -0.009 -0.269 2.873E-02 -2.178E-02 -3.198E-03 20.0 0.336 0.946 -0.3278 1.004 -0.008 -0.326 2.592E-02 -2.052E-02 -2.897E-03 24.0 0.455 1.066 -0.4036 1.159 -0.018 -0.348 3.396E-02 -1.740E-02 -2.764E-03 0 ALPHA Q/QINF EPSLON D(EPSLON)/D(ALPHA) 0 -2.0 0.944 -1.234 0.617 0.0 0.909 0.000 0.617 2.0 0.944 1.234 0.603 4.0 0.995 2.413 0.572 8.0 1.000 4.565 0.493 12.0 1.000 6.358 0.361 16.0 1.000 7.452 0.162 20.0 1.000 7.650 -0.065 24.0 1.000 6.929 -0.180 0*NOTE* OUTPUT REFLECTS EXPERIMENTAL DATA INPUTS 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING-BODY-HORIZONTAL TAIL-VERTICAL TAIL-TWIN VERTICAL PANEL CONFIGURATION INCLUDES BODY AND WING-BODY EXPERIMENTAL DATA, EXAMPLE PROBLEM 3, CASE 3 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.800 6.4000E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.021 -0.153 NDM -0.153 0.016 0.038 6.390E-02 2.441E-03 NDM NDM NDM 0.0 NDM 2.0 NDM 4.0 NDM 8.0 NDM 12.0 NDM 16.0 NDM 20.0 NDM 24.0 NDM 0 ALPHA Q/QINF EPSLON D(EPSLON)/D(ALPHA) 0 -2.0 0.914 0.000 0.639 0.0 2.0 4.0 8.0 12.0 16.0 20.0 24.0 0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST 0*NOTE* OUTPUT REFLECTS EXPERIMENTAL DATA INPUTS 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CONFIGURATION AUXILIARY AND PARTIAL OUTPUT WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION INCLUDES BODY AND WING-BODY EXPERIMENTAL DATA, EXAMPLE PROBLEM 3, CASE 3 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.800 6.4000E+06 2.250 0.822 3.000 2.600 0.000 BASIC BODY PROPERTIES WETTED AREA XCG ZCG BASE AREA ZERO LIFT DRAG BASE DRAG FRICTION DRAG PRESSURE DRAG 0.5035E+01 2.60 0.00 0.0598 0.7576E-02 0.1690E-02 0.5487E-02 0.3992E-03 XCG RELATIVE TO THEORETICAL LEADING EDGE MAC= 0.20 BASIC PLANFORM PROPERTIES TAPER ASPECT QUARTER CHORD QUARTER CHORD ZERO LIFT FRICTION AREA RATIO RATIO SWEEP MAC X(MAC) Y(MAC) DRAG COEFFICIENT 0 WING TOTAL THEORITICAL + 0.2259E+01 0.298 0.3984E+01 45.000 0.826E+00 0.260E+01 0.615E+00 TOTAL EXPOSED + 0.1796E+01 0.331 0.3707E+01 45.000 0.755E+00 0.274E+01 0.747E+00 0.774E-02 0.335E-02 0 HORIZONTAL TAIL TOTAL THEORITICAL + 0.4509E+00 0.602 0.3982E+01 45.000 0.343E+00 0.434E+01 0.307E+00 TOTAL EXPOSED + 0.3305E+00 0.661 0.3272E+01 45.000 0.322E+00 0.443E+01 0.392E+00 0.130E-02 0.391E-02 0 VERTICAL TAIL TOTAL THEORITICAL + 0.6113E+00 0.412 0.1179E+01 28.100 0.762E+00 0.379E+01 0.366E+00 TOTAL EXPOSED + 0.4048E+00 0.485 0.9804E+00 28.100 0.668E+00 0.386E+01 0.498E+00 NA NA 0*** NA PRINTED WHEN METHOD NOT APPLICABLE 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CONFIGURATION AUXILIARY AND PARTIAL OUTPUT WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION INCLUDES BODY AND WING-BODY EXPERIMENTAL DATA, EXAMPLE PROBLEM 3, CASE 3 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.800 6.4000E+06 2.250 0.822 3.000 2.600 0.000 0 CLA-B(W)= 7.443E-03 CLA-W(B)= 5.609E-02 K-B(W)= 1.476E-01 K-W(B)= 1.112E+00 XAC/C-B(W)= 6.820E-01 0 CLA-B(H)= 1.777E-03 CLA-H(B)= 1.005E-02 K-B(H)= 2.094E-01 K-H(B)= 1.184E+00 XAC/C-B(H)= 4.272E-01 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CONFIGURATION AUXILIARY AND PARTIAL OUTPUT WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION INCLUDES BODY AND WING-BODY EXPERIMENTAL DATA, EXAMPLE PROBLEM 3, CASE 3 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.800 6.4000E+06 2.250 0.822 3.000 2.600 0.000 *** WING DATA FAIRING *** CDL/CL**2 = 0.1977E+00 CLB/CL =-0.5165E-02 FORCE BREAK MACH NUMBER (ZERO SWEEP) = 0.9321E+00 FORCE BREAK MACH NUMBER (WITH SWEEP) = 0.9552E+00 MACH(A) = 1.025 CLA(A) = 0.5384E-01 MACH(B) = 1.095 CLA(B) = 0.4967E-01 (CLB/CL)M=0.6 =-0.4771E-02 (CLB/CL)M=1.4 =-0.2642E-02 LIFT-CURVE-SLOPE INTERPOLATION TABLE MACH CL-ALPHA 0.750 0.4868E-01 0.955 0.5710E-01 1.025 0.5384E-01 1.095 0.4967E-01 1.400 0.4200E-01 *** WING-BODY DATA FAIRING *** CLB/CL =-0.6150E-02 (CLB/CL)MFB =-0.4718E-02 (CLB/CL)M=1.4 =-0.2043E-02 (CNA)M=1.4 = 0.5406E-01 *** HORIZONTAL TAIL DATA FAIRING *** CDL/CL**2 = 0.2357E+00 CLB/CL =-0.2349E-02 FORCE BREAK MACH NUMBER (ZERO SWEEP) = 0.9738E+00 FORCE BREAK MACH NUMBER (WITH SWEEP) = 0.9838E+00 MACH(A) = 1.054 CLA(A) = 0.9185E-02 MACH(B) = 1.124 CLA(B) = 0.8436E-02 (CLB/CL)M=0.6 =-0.2620E-02 (CLB/CL)M=1.4 =-0.2496E-03 LIFT-CURVE-SLOPE INTERPOLATION TABLE MACH CL-ALPHA 0.750 0.8234E-02 0.984 0.9696E-02 1.054 0.9185E-02 1.124 0.8436E-02 1.400 0.7109E-02 *** HORIZONTAL TAIL-BODY DATA FAIRING *** CLB/CL =-0.2669E-02 (CLB/CL)MFB =-0.9533E-03 (CLB/CL)M=1.4 =-0.1640E-03 (CNA)M=1.4 = 0.1058E-01 *** BODY-WING-HORIZONTAL TAIL DATA FAIRING *** DRAG DIVERGENCE MACH NUMBER = 0.931 MACH CDO 0.600 0.1702E-01 0.700 0.1701E-01 1.100 0.2431E-01 1.400 0.2415E-01 1 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING-BODY-HORIZONTAL TAIL-VERTICAL TAIL-TWIN VERTICAL PANEL CONFIGURATION INCLUDES BODY AND WING-BODY EXPERIMENTAL DATA, EXAMPLE PROBLEM 3, CASE 3 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 1.500 9.9600E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.026 -0.111 0.0491 -0.112 0.022 -0.440 5.481E-02 -2.457E-02 -1.326E-02 3.486E-03 -1.944E-03 0.0 0.023 0.000 0.0000 0.000 0.023 ****** 5.454E-02 -2.402E-02 -1.928E-03 2.0 0.026 0.111 -0.0491 0.112 0.022 -0.440 5.480E-02 -2.455E-02 -1.909E-03 4.0 0.034 0.224 -0.0984 0.226 0.018 -0.435 5.480E-02 -2.459E-02 -1.890E-03 8.0 0.067 0.453 -0.1978 0.458 0.003 -0.432 5.479E-02 -2.473E-02 -1.845E-03 12.0 0.120 0.676 -0.3011 0.686 -0.023 -0.439 5.488E-02 -2.510E-02 -1.780E-03 16.0 0.190 0.883 -0.4105 0.902 -0.060 -0.455 5.506E-02 -2.566E-02 -1.685E-03 20.0 0.274 1.073 -0.5255 1.102 -0.110 -0.477 5.532E-02 -2.628E-02 -1.546E-03 24.0 0.367 1.248 -0.6420 1.290 -0.172 -0.498 5.559E-02 -2.675E-02 -1.350E-03 0 ALPHA Q/QINF EPSLON D(EPSLON)/D(ALPHA) 0 -2.0 0.964 -0.717 0.358 0.0 0.915 0.000 0.358 2.0 0.964 0.717 0.359 4.0 0.963 1.437 0.359 8.0 0.943 2.858 0.346 12.0 0.921 4.202 0.319 16.0 0.901 5.413 0.280 20.0 0.884 6.445 0.231 24.0 0.865 7.259 0.176 0**NOTE*LATERAL STABILITY DERIVATIVES DO NOT INCLUDE THE EFFECTS OF TWIN VERTICAL PANELS. (NO DATCOM METHODS) 1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE. 0 $FLTCON NMACH=1.0,MACH(1)=.6,RNNUB(1)=2.28E6$ $PROPWR AIETLP=2.0,NENGSP=1.0,THSTCP=0.15,PHALOC=0.0,PHVLOC=0.0,PRPRAD=0.40, ENGFCT=70.0,NOPBPE=4.0,BAPR75=18.0,YP=0.0,CROT=.FALSE.$ CASEID INCLUDES BODY AND WING-BODY EXPERIMENTAL DATA, EXAMPLE PROBLEM 3, CASE 4 SAVE NEXT CASE 0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING-BODY-HORIZONTAL TAIL-VERTICAL TAIL-TWIN VERTICAL PANEL CONFIGURATION PROPELLER POWER EFFECTS INCLUDED IN THE LONGITUDINAL STABILITY RESULTS INCLUDES BODY AND WING-BODY EXPERIMENTAL DATA, EXAMPLE PROBLEM 3, CASE 4 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 2.2800E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.024 -0.137 0.0355 -0.138 0.020 -0.258 6.185E-02 -1.474E-02 -2.237E-02 6.088E-03 -1.477E-03 0.0 0.023 0.001 0.0072 0.001 0.023 7.658 6.184E-02 -1.476E-02 -1.755E-03 2.0 0.027 0.138 -0.0203 0.139 0.023 -0.146 6.226E-02 -1.570E-02 -2.030E-03 4.0 0.038 0.275 -0.0503 0.277 0.018 -0.182 6.365E-02 -1.683E-02 -2.304E-03 8.0 0.099 0.548 -0.1066 0.556 0.022 -0.192 5.845E-02 -1.138E-02 -2.894E-03 12.0 0.200 0.749 -0.0974 0.774 0.040 -0.126 4.345E-02 -1.365E-02 -3.210E-03 16.0 0.309 0.891 -0.1494 0.941 0.051 -0.159 2.880E-02 -2.217E-02 -3.198E-03 20.0 0.436 0.975 -0.1980 1.065 0.077 -0.186 2.597E-02 -2.099E-02 -2.897E-03 24.0 0.587 1.091 -0.2354 1.236 0.092 -0.191 3.393E-02 -1.777E-02 -2.764E-03 0 ALPHA Q/QINF EPSLON D(EPSLON)/D(ALPHA) 0 -2.0 0.937 -1.234 0.617 0.0 0.904 0.000 0.617 2.0 0.937 1.234 0.603 4.0 0.991 2.413 0.572 8.0 1.000 4.565 0.493 12.0 1.000 6.358 0.359 16.0 1.000 7.435 0.152 20.0 1.000 7.576 -0.084 24.0 1.000 6.766 -0.202 0*NOTE* OUTPUT REFLECTS EXPERIMENTAL DATA INPUTS 1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE. 0 $FLTCON NMACH=1.0,MACH(1)=.6,RNNUB(1)=2.28E6$ $JETPWR AIETLJ=2.0,NENGSJ=1.0,THSTCJ=.35,JIALOC=0.0,JEVLOC=0.0,JEALOC=0.5, JINLTA=3.0,JEANGL=15.0,JEVELO=4000.,AMBTMP=500.,JESTMP=2000.,JELLOC=0.0, JETOTP=5000.,AMBSTP=500.,JERAD=2.0$ CASEID INCLUDES BODY AND WING-BODY EXPERIMENTAL DATA, EXAMPLE PROBLEM 3, CASE 5 NEXT CASE 0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING-BODY-HORIZONTAL TAIL-VERTICAL TAIL-TWIN VERTICAL PANEL CONFIGURATION JET POWER EFFECTS INCLUDED IN THE LONGITUDINAL STABILITY RESULTS INCLUDES BODY AND WING-BODY EXPERIMENTAL DATA, EXAMPLE PROBLEM 3, CASE 5 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 2.2800E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.019 -0.119 0.0252 -0.120 0.014 -0.210 6.185E-02 -1.474E-02 -2.237E-02 6.088E-03 -1.477E-03 0.0 0.017 0.114 0.3066 0.114 0.017 2.684 6.184E-02 -1.476E-02 -1.755E-03 2.0 0.019 0.348 0.5862 0.349 0.006 1.680 6.226E-02 -1.570E-02 -2.030E-03 4.0 0.023 0.584 0.8608 0.584 -0.018 1.473 6.365E-02 -1.683E-02 -2.304E-03 8.0 0.071 1.065 1.4056 1.064 -0.078 1.320 5.845E-02 -1.138E-02 -2.894E-03 12.0 0.154 1.485 1.9890 1.485 -0.158 1.339 4.345E-02 -1.365E-02 -3.210E-03 16.0 0.239 1.839 2.4962 1.834 -0.277 1.361 2.880E-02 -2.217E-02 -3.198E-03 20.0 0.339 2.133 2.9851 2.120 -0.411 1.408 2.597E-02 -2.099E-02 -2.897E-03 24.0 0.460 2.453 3.4690 2.428 -0.578 1.429 3.393E-02 -1.777E-02 -2.764E-03 0 ALPHA Q/QINF EPSLON D(EPSLON)/D(ALPHA) 0 -2.0 0.937 -1.234 0.617 0.0 0.904 0.000 0.617 2.0 0.937 1.234 0.603 4.0 0.991 2.413 0.572 8.0 1.000 4.565 0.493 12.0 1.000 6.358 0.359 16.0 1.000 7.435 0.152 20.0 1.000 7.576 -0.084 24.0 1.000 6.766 -0.202 0*NOTE* OUTPUT REFLECTS EXPERIMENTAL DATA INPUTS 1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE. 0 $FLTCON NMACH=1.0,MACH(1)=0.60,NALPHA=5.,ALSCHD(1)=0.0,5.0,10.0,15.0,20.0, RNNUB(1)=3.1E6$ $OPTINS SREF=694.2,CBARR=18.07,BLREF=45.6$ $SYNTHS XCG=36.68,ZCG=0.0$ $BODY NX=19.0,BNOSE=2.0,BTAIL=2.0,BLN=30.0,BLA=0.0, X(1)=0.0,2.01,5.49,8.975,12.47,15.97,19.47,22.89,26.49,30.0,33.51,37.02, 40.53,44.03,47.53,51.02,54.52,57.99,60.0, S(1)=0.0,2.89,7.42,11.32,14.64,17.36,19.49,21.0,21.91,22.20,21.90, 21.0,19.49,17.36,14.64,12.33,7.42,2.89,0.0, P(1)=0.0,1.84,4.72,7.21,9.32,11.05,12.41,13.36,13.94,14.14,13.94, 13.36,12.41,11.05,9.32,7.21,4.72,1.84,0.0, R(1)=0.0,.293,.752,1.15,1.48,1.76,1.97,2.13,2.22,2.25,2.22,2.13,1.97,1.76, 1.48,1.15,.752,.293,0.0,$ NACA-W-6-65A004 NACA-H-6-65A004 $WGPLNF CHSTAT=0.0, TWISTA=0.0,SSPNDD=0.0,DHDADI=0.0,DHDADO=0.0,TYPE=1.0$ $SYNTHS XW=8.064,ZW=0.0,ALIW=0.0$ $WGPLNF CHRDTP=0.0,SSPNE=6.205,SSPN=8.01,CHRDR=13.87,SAVSI=60.0$ $SYNTHS XH=29.42,ZH=0.0,ALIH=0.0$ $HTPLNF SSPNE=21.34,SSPN=22.82,CHRDR=26.62,SAVSI=38.52,CHSTAT=0.0, CHRDTP=3.80, TWISTA=0.0,SSPNDD=0.0,DHDADI=0.0,DHDADO=0.0,TYPE=1.0,SHB(1)=73.5, SEXT(1)=73.5,RLPH(1)=47.3$ CASEID BODY PLUS WING PLUS CANARD, EXAMPLE PROBLEM 4, CASE 1 NEXT CASE 0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM WING SECTION DEFINITION 0 IDEAL ANGLE OF ATTACK = 0.00000 DEG. ZERO LIFT ANGLE OF ATTACK = 0.00000 DEG. IDEAL LIFT COEFFICIENT = 0.00000 ZERO LIFT PITCHING MOMENT COEFFICIENT = 0.00000 MACH ZERO LIFT-CURVE-SLOPE = 0.10052 /DEG. LEADING EDGE RADIUS = 0.00112 FRACTION CHORD MAXIMUM AIRFOIL THICKNESS = 0.04000 FRACTION CHORD DELTA-Y = 0.83905 PERCENT CHORD 0 MACH= 0.6000 LIFT-CURVE-SLOPE = 0.13607 /DEG. XAC = 0.25741 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM HORIZONTAL TAIL SECTION DEFINITION 0 IDEAL ANGLE OF ATTACK = 0.00000 DEG. ZERO LIFT ANGLE OF ATTACK = 0.00000 DEG. IDEAL LIFT COEFFICIENT = 0.00000 ZERO LIFT PITCHING MOMENT COEFFICIENT = 0.00000 MACH ZERO LIFT-CURVE-SLOPE = 0.10052 /DEG. LEADING EDGE RADIUS = 0.00112 FRACTION CHORD MAXIMUM AIRFOIL THICKNESS = 0.04000 FRACTION CHORD DELTA-Y = 0.83905 PERCENT CHORD 0 MACH= 0.6000 LIFT-CURVE-SLOPE = 0.13733 /DEG. XAC = 0.25734 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING-BODY-HORIZONTAL TAIL CONFIGURATION BODY PLUS WING PLUS CANARD, EXAMPLE PROBLEM 4, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 3.1000E+06 694.200 18.070 45.600 36.680 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 0.0 0.007 0.000 0.0000 0.000 0.007 ****** 5.841E-02 -4.250E-03 -3.690E-04 -6.036E-04 0.000E+00 5.0 0.020 0.306 -0.0242 0.307 -0.007 -0.079 6.028E-02 -4.346E-03 -7.737E-04 10.0 0.054 0.603 -0.0435 0.603 -0.051 -0.072 4.872E-02 -1.013E-03 -1.502E-03 15.0 0.091 0.793 -0.0344 0.790 -0.117 -0.044 2.119E-02 5.741E-03 -1.996E-03 20.0 0.104 0.815 0.0139 0.801 -0.181 0.017 -1.265E-02 1.359E-02 -2.103E-03 0NOTE - CANARD CONFIGURATION EFFECTIVE EPSOLN AND D(EPSOLN)/D(ALPHA) ARE AVAILABLE AS PARTIAL OUTPUT AND IN THE FACT ARRAY 1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE. 0 DIM M $FLTCON NMACH=1.0,MACH(1)=2.00,NALPHA=5.,ALSCHD(1)=0.0,5.0,10.0,15.0,20.0, RNNUB(1)=6.56E6,NALT=1.,ALT(1)=27400.$ $OPTINS SREF=64.4933,CBARR=5.5077,BLREF=13.9111$ $SYNTHS XCG=12.1800,ZCG=0.0,SCALE=0.30$ $BODY NX=19.0,BNOSE=2.0,BTAIL=2.0,BLN=9.144,BLA=0.0, X(1)=1.0,1.613,2.673,3.736,4.801,5.868,6.934,8.004,9.074,10.144,11.214, 12.284,13.354,14.420,15.487,16.551,17.618,18.675,19.288, S(1)=0.,.268,.689,1.052,1.360,1.613,1.811,1.951,2.036,2.062,2.085, 1.951,1.811,1.613,1.360,1.053,.689,.268,0., P(1)=0.,.561,1.439,2.198,2.841,3.368,3.783,4.072,4.249,4.310,4.249, 4.072,3.783,3.368,2.841,2.198,1.439,.561,0., R(1)=0.,.089,.229,.351,.451,.536,.600,.649,.677,.686,.677,.649,.600, .536,.451,.351,.229,.089,0.$ NACA-W-S-3-30.0-2.5-20.0 NACA-H-S-1-50.0-2.5 $WGPLNF CHSTAT=0.0, TWISTA=0.0,SSPNDD=0.0,DHDADI=0.0,DHDADO=0.0,TYPE=1.0$ $SYNTHS XW=3.4579,ZW=0.0,ALIW=0.0$ $WGPLNF CHRDTP=0.0,SSPNE=1.8913,SSPN=2.4414,CHRDR=4.2276,SAVSI=60.0$ $SYNTHS XH=9.9672,ZH=0.0,ALIH=0.0$ $HTPLNF SSPNE=6.5044,SSPN=6.9555,CHRDR=8.1138,SAVSI=38.52,CHSTAT=0.0, CHRDTP=1.1582, TWISTA=0.0,SSPNDD=0.0,DHDADI=0.0,DHDADO=0.0,TYPE=1.0,SHB(1)=6.8283, SEXT(1)=6.8284,RLPH(1)=14.4170$ CASEID BODY PLUS WING PLUS CANARD, EXAMPLE PROBLEM 4, CASE 2 NEXT CASE 0 INPUT DIMENSIONS ARE IN M , SCALE FACTOR IS 0.3000 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM WING SECTION DEFINITION 0 IDEAL ANGLE OF ATTACK = 0.00000 DEG. ZERO LIFT ANGLE OF ATTACK = 0.00000 DEG. IDEAL LIFT COEFFICIENT = 0.00000 ZERO LIFT PITCHING MOMENT COEFFICIENT = 0.00000 MACH ZERO LIFT-CURVE-SLOPE = 0.09930 /DEG. LEADING EDGE RADIUS = 0.00000 FRACTION CHORD MAXIMUM AIRFOIL THICKNESS = 0.02500 FRACTION CHORD DELTA-Y = 0.24375 PERCENT CHORD 0 *** CREST CRITICAL MACH NUMBER EXCEEDED *** CREST CRITICAL MACH = 0.85858 LOCATION = 0.30335 FRACTION CHORD LIFT-CURVE-SLOPE = 0.17772 /DEG. 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM HORIZONTAL TAIL SECTION DEFINITION 0 IDEAL ANGLE OF ATTACK = 0.00000 DEG. ZERO LIFT ANGLE OF ATTACK = 0.00000 DEG. IDEAL LIFT COEFFICIENT = 0.00000 ZERO LIFT PITCHING MOMENT COEFFICIENT = 0.00000 MACH ZERO LIFT-CURVE-SLOPE = 0.09889 /DEG. LEADING EDGE RADIUS = 0.00000 FRACTION CHORD MAXIMUM AIRFOIL THICKNESS = 0.02500 FRACTION CHORD DELTA-Y = 0.14625 PERCENT CHORD 0 *** CREST CRITICAL MACH NUMBER EXCEEDED *** CREST CRITICAL MACH = 0.87398 LOCATION = 0.46775 FRACTION CHORD LIFT-CURVE-SLOPE = 0.18773 /DEG. 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING-BODY-HORIZONTAL TAIL CONFIGURATION BODY PLUS WING PLUS CANARD, EXAMPLE PROBLEM 4, CASE 2 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT M M/SEC N/ M**2 DEG K 1/ M M**2 M M M M 0 2.000 27400.00 599.91 1.7694E+03 223.933 6.5600E+06 64.493 5.508 13.911 12.180 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 0.0 0.008 0.000 0.0000 0.000 0.008 ****** 3.726E-02 -2.030E-02 -2.266E-04 -5.046E-04 0.000E+00 5.0 0.024 0.206 -0.1159 0.207 0.006 -0.559 4.042E-02 -2.318E-02 -1.551E-06 10.0 0.078 0.425 -0.2463 0.432 0.003 -0.570 4.095E-02 -2.463E-02 -3.177E-06 15.0 0.174 0.653 -0.4042 0.676 -0.001 -0.598 4.119E-02 -2.695E-02 -4.757E-06 20.0 0.336 0.914 -0.6106 0.974 0.003 -0.627 4.117E-02 -3.053E-02 -6.165E-06 0NOTE - CANARD CONFIGURATION EFFECTIVE EPSOLN AND D(EPSOLN)/D(ALPHA) ARE AVAILABLE AS PARTIAL OUTPUT AND IN THE FACT ARRAY 1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE. 0 DIM FT PART $FLTCON NALPHA=9.0,ALSCHD(1)=-2.0,0.0,2.0,4.0,8.0, 12.0,16.0,20.0,24.0$ $FLTCON NMACH=1.0,MACH(1)=0.60,RNNUB(1)=4.26E6$ $OPTINS SREF=2.25,CBARR=0.822,BLREF=3.00$ $SYNTHS XCG=2.60,ZCG=0.0,XW=1.70,ZW=0.0,ALIW=0.0$ $BODY NX=10.0,BNOSE=2.0,BTAIL=1.0,BLN=1.46,BLA=1.97, X(1)=0.0,.175,.322,.530,.85,1.46,2.50,3.43,3.97,4.57, R(1)=0.0,.0417,.0833,.125,.1665,.208,.208,.208,.178,.138$ $WGPLNF CHRDTP=0.346,SSPNE=1.29,SSPN=1.50,CHRDR=1.16,SAVSI=45.0,CHSTAT=.25, TWISTA=0.0,SSPNDD=0.0,DHDADI=0.0,DHDADO=0.0,TYPE=1.0$ $WGSCHR TOVC=.060,DELTAY=1.30,XOVC=0.40,CLI=0.0,ALPHAI=0.0,CLALPA(1)=0.131, CLMAX(1)=.82,CM0=0.0,LERI=0.0025,CLAMO=.105,YCM=0.0$ $WGSCHR CLMAXL=.8,TCEFF=.03$ CASEID BODY-WING DAMPING DERIVATIVES, EXAMPLE PROBLEM 5, CASE 1 DAMP SAVE DUMP DYN NEXT CASE 0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000 WARNING*** BODY ALONE DYNAMIC DERIVATIVE METHOD VALID FOR NOSE CYLINDER ONLY TAIL EFFECTS IGNORED] DYN( 1)= 1.00000E-30 DYN( 2)=-1.37623E-02 DYN( 3)= 1.00000E-30 DYN( 4)= 1.00000E-30 DYN( 5)= 1.00000E-30 DYN( 6)= 1.00000E-30 DYN( 7)= 1.00000E-30 DYN( 8)= 1.00000E-30 DYN( 9)= 1.00000E-30 DYN( 10)= 1.00000E-30 DYN( 11)= 1.00000E-30 DYN( 12)= 1.00000E-30 DYN( 13)= 1.00000E-30 DYN( 14)= 1.00000E-30 DYN( 15)= 1.00000E-30 DYN( 16)= 1.00000E-30 DYN( 17)= 1.00000E-30 DYN( 18)= 1.00000E-30 DYN( 19)= 1.00000E-30 DYN( 20)= 1.00000E-30 DYN( 21)=-5.92906E-03 DYN( 22)= 1.00000E-30 DYN( 23)= 1.00000E-30 DYN( 24)= 1.00000E-30 DYN( 25)= 1.00000E-30 DYN( 26)= 1.00000E-30 DYN( 27)= 1.00000E-30 DYN( 28)= 1.00000E-30 DYN( 29)= 1.00000E-30 DYN( 30)= 1.00000E-30 DYN( 31)= 1.00000E-30 DYN( 32)= 1.00000E-30 DYN( 33)= 1.00000E-30 DYN( 34)= 1.00000E-30 DYN( 35)= 1.00000E-30 DYN( 36)= 1.00000E-30 DYN( 37)= 1.00000E-30 DYN( 38)= 1.00000E-30 DYN( 39)= 1.00000E-30 DYN( 40)= 4.78802E-01 DYN( 41)= 1.00000E-30 DYN( 42)= 1.00000E-30 DYN( 43)= 1.00000E-30 DYN( 44)= 0.00000E+00 DYN( 45)= 4.66430E-02 DYN( 46)=-1.50367E-01 DYN( 47)= 4.66430E-02 DYN( 48)= 4.66430E-02 DYN( 49)= 4.67196E-02 DYN( 50)= 4.66053E-02 DYN( 51)= 4.51855E-02 DYN( 52)= 3.82380E-02 DYN( 53)= 2.44165E-02 DYN( 54)= 7.06773E-03 DYN( 55)=-1.18053E-02 DYN( 56)= 1.00000E-30 DYN( 57)= 1.00000E-30 DYN( 58)= 1.00000E-30 DYN( 59)= 1.00000E-30 DYN( 60)= 1.00000E-30 DYN( 61)= 1.00000E-30 DYN( 62)= 1.00000E-30 DYN( 63)= 1.00000E-30 DYN( 64)= 1.00000E-30 DYN( 65)= 1.00000E-30 DYN( 66)= 1.00000E-30 DYN( 67)= 0.00000E+00 DYN( 68)= 1.00000E+00 DYN( 69)=-3.86146E-02 DYN( 70)= 3.33513E+00 DYN( 71)=-2.45063E-01 DYN( 72)=-1.13060E-03 DYN( 73)=-7.97236E-04 DYN( 74)=-1.13060E-03 DYN( 75)=-2.13507E-03 DYN( 76)=-6.09192E-03 DYN( 77)=-1.23164E-02 DYN( 78)=-1.83898E-02 DYN( 79)=-2.19844E-02 DYN( 80)=-2.14480E-02 DYN( 81)= 1.00000E-30 DYN( 82)= 1.00000E-30 DYN( 83)= 1.00000E-30 DYN( 84)= 1.00000E-30 DYN( 85)= 1.00000E-30 DYN( 86)= 1.00000E-30 DYN( 87)= 1.00000E-30 DYN( 88)= 1.00000E-30 DYN( 89)= 1.00000E-30 DYN( 90)= 1.00000E-30 DYN( 91)= 1.00000E-30 DYN( 92)=-1.55970E-01 DYN( 93)= 9.05538E-01 DYN( 94)= 6.40340E-03 DYN( 95)=-2.42434E-04 DYN( 96)=-1.62232E-03 DYN( 97)= 1.00000E-30 DYN( 98)= 3.25393E-03 DYN( 99)= 6.50914E-03 DYN(100)= 1.28847E-02 DYN(101)= 1.76882E-02 DYN(102)= 1.91888E-02 DYN(103)= 1.65058E-02 DYN(104)= 1.39972E-02 DYN(105)= 1.00000E-30 DYN(106)= 1.00000E-30 DYN(107)= 1.00000E-30 DYN(108)= 1.00000E-30 DYN(109)= 1.00000E-30 DYN(110)= 1.00000E-30 DYN(111)= 1.00000E-30 DYN(112)= 1.00000E-30 DYN(113)= 1.00000E-30 DYN(114)= 1.00000E-30 DYN(115)= 1.00000E-30 DYN(116)=-1.02747E-03 DYN(117)= 1.00000E-30 DYN(118)= 2.06168E-03 DYN(119)= 4.09652E-03 DYN(120)= 7.84501E-03 DYN(121)= 9.47594E-03 DYN(122)= 7.44953E-03 DYN(123)= 2.35639E-03 DYN(124)=-8.26683E-04 DYN(125)= 1.00000E-30 DYN(126)= 1.00000E-30 DYN(127)= 1.00000E-30 DYN(128)= 1.00000E-30 DYN(129)= 1.00000E-30 DYN(130)= 1.00000E-30 DYN(131)= 1.00000E-30 DYN(132)= 1.00000E-30 DYN(133)= 1.00000E-30 DYN(134)= 1.00000E-30 DYN(135)= 1.00000E-30 DYN(136)=-3.44874E-04 DYN(137)= 1.00000E-30 DYN(138)= 6.92013E-04 DYN(139)= 1.37501E-03 DYN(140)= 2.63321E-03 DYN(141)= 3.18064E-03 DYN(142)= 2.50046E-03 DYN(143)= 7.90931E-04 DYN(144)=-2.77479E-04 DYN(145)= 1.00000E-30 DYN(146)= 1.00000E-30 DYN(147)= 1.00000E-30 DYN(148)= 1.00000E-30 DYN(149)= 1.00000E-30 DYN(150)= 1.00000E-30 DYN(151)= 1.00000E-30 DYN(152)= 1.00000E-30 DYN(153)= 1.00000E-30 DYN(154)= 1.00000E-30 DYN(155)= 1.00000E-30 DYN(156)= 4.65658E-01 DYN(157)= 1.00000E+00 DYN(158)= 4.65373E-01 DYN(159)= 4.69919E-01 DYN(160)= 4.91608E-01 DYN(161)= 5.66067E-01 DYN(162)= 7.03442E-01 DYN(163)= 9.00384E-01 DYN(164)= 1.03847E+00 DYN(165)= 1.00000E-30 DYN(166)= 1.00000E-30 DYN(167)= 1.00000E-30 DYN(168)= 1.00000E-30 DYN(169)= 1.00000E-30 DYN(170)= 1.00000E-30 DYN(171)= 1.00000E-30 DYN(172)= 1.00000E-30 DYN(173)= 1.00000E-30 DYN(174)= 1.00000E-30 DYN(175)= 1.00000E-30 DYN(176)=-2.92747E-01 DYN(177)= 0.00000E+00 DYN(178)= 4.84686E-01 DYN(179)= 2.01527E+00 DYN(180)= 5.64482E-01 DYN(181)= 2.14793E+00 DYN(182)=-2.85688E-03 DYN(183)=-5.37371E-01 DYN(184)= 7.74307E-03 DYN(185)= 6.37788E-03 DYN(186)= 7.74307E-03 DYN(187)= 1.18566E-02 DYN(188)= 2.80606E-02 DYN(189)= 5.35510E-02 DYN(190)= 7.84230E-02 DYN(191)= 9.31435E-02 DYN(192)= 9.09467E-02 DYN(193)= 1.00000E-30 DYN(194)= 1.00000E-30 DYN(195)= 1.00000E-30 DYN(196)= 1.00000E-30 DYN(197)= 1.00000E-30 DYN(198)= 1.00000E-30 DYN(199)= 1.00000E-30 DYN(200)= 1.00000E-30 DYN(201)= 1.00000E-30 DYN(202)= 1.00000E-30 DYN(203)= 1.00000E-30 DYN(204)= 1.00000E-30 DYN(205)= 1.00000E-30 DYN(206)= 1.00000E-30 DYN(207)= 1.00000E-30 DYN(208)= 1.00000E-30 DYN(209)= 1.00000E-30 DYN(210)= 1.00000E-30 DYN(211)= 1.00000E-30 DYN(212)= 1.00000E-30 DYN(213)= 1.00000E-30 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING-BODY CONFIGURATION BODY-WING DAMPING DERIVATIVES, EXAMPLE PROBLEM 5, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 4.2600E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.016 -0.125 0.0032 -0.126 0.012 -0.026 6.258E-02 -1.352E-03 -1.612E-03 -1.845E-03 5.509E-04 0.0 0.015 0.000 0.0000 0.000 0.015 ****** 6.258E-02 -1.864E-03 5.528E-12 2.0 0.016 0.125 -0.0042 0.126 0.012 -0.034 6.273E-02 -2.646E-03 -5.509E-04 4.0 0.024 0.251 -0.0106 0.252 0.006 -0.042 6.269E-02 -3.674E-03 -1.104E-03 8.0 0.067 0.500 -0.0293 0.505 -0.003 -0.058 6.082E-02 -4.565E-03 -2.201E-03 12.0 0.149 0.738 -0.0471 0.752 -0.007 -0.063 5.089E-02 -3.125E-03 -3.246E-03 16.0 0.236 0.907 -0.0543 0.937 -0.023 -0.058 3.176E-02 -1.423E-03 -3.993E-03 20.0 0.992 -0.0585 9.201E-03 -1.326E-04 -4.364E-03 24.0 0.981 -0.0554 -1.458E-02 1.698E-03 -4.317E-03 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM DYNAMIC DERIVATIVES WING-BODY CONFIGURATION BODY-WING DAMPING DERIVATIVES, EXAMPLE PROBLEM 5, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 4.2600E+06 2.250 0.822 3.000 2.600 0.000 DYNAMIC DERIVATIVES (PER DEGREE) 0 -------PITCHING------- -----ACCELERATION------ --------------ROLLING-------------- --------YAWING-------- 0 ALPHA CLQ CMQ CLAD CMAD CLP CYP CNP CNR CLR 0 -2.00 4.840E-02 -1.968E-02 NDM NDM -5.150E-03 -4.280E-04 1.791E-05 -7.334E-05 -6.158E-04 0.00 -5.144E-03 0.000E+00 0.000E+00 -6.006E-05 0.000E+00 2.00 -5.158E-03 4.277E-04 -1.763E-05 -7.334E-05 6.158E-04 4.00 -5.163E-03 8.652E-04 -3.909E-05 -1.134E-04 1.234E-03 8.00 -5.076E-03 1.801E-03 -1.170E-04 -2.711E-04 2.454E-03 12.00 -4.421E-03 3.058E-03 -4.068E-04 -5.192E-04 3.620E-03 16.00 -3.008E-03 4.697E-03 -9.953E-04 -7.613E-04 4.473E-03 20.00 -1.163E-03 6.597E-03 -1.715E-03 -9.045E-04 4.909E-03 24.00 9.225E-04 7.512E-03 -1.985E-03 -8.832E-04 4.847E-03 0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CONFIGURATION AUXILIARY AND PARTIAL OUTPUT WING-BODY CONFIGURATION BODY-WING DAMPING DERIVATIVES, EXAMPLE PROBLEM 5, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 4.2600E+06 2.250 0.822 3.000 2.600 0.000 BASIC BODY PROPERTIES WETTED AREA XCG ZCG BASE AREA ZERO LIFT DRAG BASE DRAG FRICTION DRAG PRESSURE DRAG 0.5043E+01 2.60 0.00 0.0598 0.7862E-02 0.1587E-02 0.6275E-02 NA XCG RELATIVE TO THEORETICAL LEADING EDGE MAC= 0.20 BASIC PLANFORM PROPERTIES TAPER ASPECT QUARTER CHORD QUARTER CHORD ZERO LIFT FRICTION AREA RATIO RATIO SWEEP MAC X(MAC) Y(MAC) DRAG COEFFICIENT 0 WING TOTAL THEORITICAL + 0.2259E+01 0.298 0.3984E+01 45.000 0.826E+00 0.260E+01 0.615E+00 TOTAL EXPOSED + 0.1796E+01 0.331 0.3707E+01 45.000 0.755E+00 0.274E+01 0.747E+00 0.640E-02 0.350E-02 0*** NA PRINTED WHEN METHOD NOT APPLICABLE 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CONFIGURATION AUXILIARY AND PARTIAL OUTPUT WING-BODY CONFIGURATION BODY-WING DAMPING DERIVATIVES, EXAMPLE PROBLEM 5, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 4.2600E+06 2.250 0.822 3.000 2.600 0.000 0 CLA-B(W)= 9.008E-03 CLA-W(B)= 5.163E-02 K-B(W)= 1.940E-01 K-W(B)= 1.112E+00 XAC/C-B(W)= 6.055E-01 ALPHA IV-B(W) IV-W(H) IV-B(H) GAMMA/ GAMMA/ 2*PI*ALPHA*V*R (2*PI*ALPHA*V*R)T -2.000 0.0000E+00 NA NA 0.0000E+00 NA 0.000 0.0000E+00 NA NA 0.0000E+00 NA 2.000 0.0000E+00 NA NA 0.0000E+00 NA 4.000 0.0000E+00 NA NA 0.0000E+00 NA 8.000 0.0000E+00 NA NA NDM NA 12.000 -0.4968E-01 NA NA 0.4592E+00 NA 16.000 -0.1582E+00 NA NA 0.6247E+00 NA 20.000 -0.2150E+00 NA NA 0.7942E+00 NA 24.000 -0.2302E+00 NA NA 0.8727E+00 NA DYNAMIC DERIVATIVE INCREMENTALS CLP(GAMMA=CL=0) =-2.9275E-01 CLP(GAMMA)/CLP (GAMMA=0) = 1.0000E+00 CNP/THETA =-2.4243E-04 CYP/GAMMA = 0.0000E+00 CYP/CL (CL=0) = 5.6448E-01 CLB/GAMMA (CMO/THETA)W (CMO/THETA)H -0.1399E-03 NA NA 0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST 0*** NA PRINTED WHEN METHOD NOT APPLICABLE 1 1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE. 0 $SYMFLP NDELTA=6.0,DELTA(1)=0.,10.,20.,30.,40.,60.,PHETE=.0522,CHRDFI=.2094, CHRDFO=.1554,SPANFI=.208,SPANFO=.708,FTYPE=1.0,CB=.01125,TC=.0225, PHETEP=.0391,NTYPE=1.$ CASEID PLAIN FLAPS ON WING, EXAMPLE PROBLEM 5, CASE 2 DUMP FCM NEXT CASE 0ERROR ** FLAP INBOARD SPAN, SPANI = 0.20800E+00, IT IS INSIDE THE BODY AS DEFINED BY SSPN AND SSPNE SPANI IS REDEFINED, SPANI = SSPN-SSPNE = 0.21000E+00 0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING-BODY CONFIGURATION PLAIN FLAPS ON WING, EXAMPLE PROBLEM 5, CASE 2 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 4.2600E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.016 -0.125 0.0032 -0.126 0.012 -0.026 6.258E-02 -1.352E-03 -1.612E-03 -1.845E-03 5.509E-04 0.0 0.015 0.000 0.0000 0.000 0.015 ****** 6.258E-02 -1.864E-03 5.528E-12 2.0 0.016 0.125 -0.0042 0.126 0.012 -0.034 6.273E-02 -2.646E-03 -5.509E-04 4.0 0.024 0.251 -0.0106 0.252 0.006 -0.042 6.269E-02 -3.674E-03 -1.104E-03 8.0 0.067 0.500 -0.0293 0.505 -0.003 -0.058 6.082E-02 -4.565E-03 -2.201E-03 12.0 0.149 0.738 -0.0471 0.752 -0.007 -0.063 5.089E-02 -3.125E-03 -3.246E-03 16.0 0.236 0.907 -0.0543 0.937 -0.023 -0.058 3.176E-02 -1.423E-03 -3.993E-03 20.0 0.992 -0.0585 9.201E-03 -1.326E-04 -4.364E-03 24.0 0.981 -0.0554 -1.458E-02 1.698E-03 -4.317E-03 FCM( 1)= 5.13402E+01 FCM( 2)= 5.17030E+00 FCM( 3)= 3.74516E+00 FCM( 4)= 2.65321E+00 FCM( 5)= 1.97316E+00 FCM( 6)= 6.96020E-01 FCM( 7)= 0.00000E+00 FCM( 8)= 1.40000E-01 FCM( 9)= 1.42300E-01 FCM( 10)= 2.81700E-01 FCM( 11)= 4.15300E-01 FCM( 12)= 4.72000E-01 FCM( 13)= 5.40700E-01 FCM( 14)= 6.54900E-01 FCM( 15)= 7.55700E-01 FCM( 16)= 8.41200E-01 FCM( 17)= 9.09700E-01 FCM( 18)= 9.59500E-01 FCM( 19)= 9.89800E-01 FCM( 20)= 1.00000E+00 FCM( 21)=-1.91186E-02 FCM( 22)=-2.34326E-02 FCM( 23)=-2.35110E-02 FCM( 24)=-2.81482E-02 FCM( 25)=-3.12759E-02 FCM( 26)=-3.00328E-02 FCM( 27)=-2.83284E-02 FCM( 28)=-2.24167E-02 FCM( 29)=-1.70822E-02 FCM( 30)=-1.33461E-02 FCM( 31)=-1.12025E-02 FCM( 32)=-6.07483E-03 FCM( 33)=-1.62186E-03 FCM( 34)= 0.00000E+00 FCM( 35)= 2.15990E-01 FCM( 36)= 1.76124E-01 FCM( 37)= 1.75469E-01 FCM( 38)= 1.26859E-01 FCM( 39)= 8.16612E-02 FCM( 40)= 7.12404E-02 FCM( 41)= 5.86140E-02 FCM( 42)= 4.53843E-02 FCM( 43)= 3.55930E-02 FCM( 44)= 2.77490E-02 FCM( 45)= 1.97556E-02 FCM( 46)= 9.63844E-03 FCM( 47)= 2.42747E-03 FCM( 48)= 0.00000E+00 FCM( 49)= 4.38054E-01 FCM( 50)= 4.22795E-01 FCM( 51)= 4.22544E-01 FCM( 52)= 3.92166E-01 FCM( 53)= 3.43968E-01 FCM( 54)= 3.09885E-01 FCM( 55)= 2.68588E-01 FCM( 56)= 1.91640E-01 FCM( 57)= 1.33660E-01 FCM( 58)= 9.54978E-02 FCM( 59)= 7.06580E-02 FCM( 60)= 3.48899E-02 FCM( 61)= 8.78712E-03 FCM( 62)= 0.00000E+00 FCM( 63)=-3.81781E-01 FCM( 64)=-3.81781E-01 FCM( 65)=-3.32116E-01 FCM( 66)=-2.56890E-01 FCM( 67)=-2.27116E-01 FCM( 68)=-1.90857E-01 FCM( 69)=-3.81781E-01 FCM( 70)= 1.00000E-30 FCM( 71)= 1.00000E-30 FCM( 72)= 1.00000E-30 FCM( 73)= 1.04604E+00 FCM( 74)= 9.48034E-01 FCM( 75)= 9.46424E-01 FCM( 76)= 8.48839E-01 FCM( 77)= 7.55313E-01 FCM( 78)= 7.15621E-01 FCM( 79)= 6.67528E-01 FCM( 80)= 5.87584E-01 FCM( 81)= 5.17020E-01 FCM( 82)= 4.57166E-01 FCM( 83)= 4.09214E-01 FCM( 84)= 3.74352E-01 FCM( 85)= 3.53140E-01 FCM( 86)= 3.46000E-01 FCM( 87)= 2.22064E-01 FCM( 88)= 2.46671E-01 FCM( 89)= 2.47075E-01 FCM( 90)= 2.65307E-01 FCM( 91)= 2.62307E-01 FCM( 92)= 2.38644E-01 FCM( 93)= 2.09974E-01 FCM( 94)= 1.46256E-01 FCM( 95)= 9.80673E-02 FCM( 96)= 6.77488E-02 FCM( 97)= 5.09024E-02 FCM( 98)= 2.52515E-02 FCM( 99)= 6.35965E-03 FCM(100)= 0.00000E+00 FCM(101)= 1.20000E-01 FCM(102)= 1.00000E-30 FCM(103)= 1.00000E-30 FCM(104)= 1.00000E-30 FCM(105)= 1.00000E-30 FCM(106)= 1.00000E-30 FCM(107)= 5.86700E-01 FCM(108)= 1.53900E-02 FCM(109)= 0.00000E+00 FCM(110)= 0.00000E+00 FCM(111)= 0.00000E+00 FCM(112)= 0.00000E+00 FCM(113)= 0.00000E+00 FCM(114)= 1.00000E-30 FCM(115)= 1.93849E+00 FCM(116)= 2.14359E+00 FCM(117)= 2.14696E+00 FCM(118)= 2.35118E+00 FCM(119)= 2.54691E+00 FCM(120)= 2.62997E+00 FCM(121)= 2.73062E+00 FCM(122)= 2.89792E+00 FCM(123)= 3.04560E+00 FCM(124)= 3.17086E+00 FCM(125)= 3.27121E+00 FCM(126)= 3.34417E+00 FCM(127)= 3.38856E+00 FCM(128)= 3.40350E+00 FCM(129)= 0.00000E+00 FCM(130)= 2.20878E-01 FCM(131)= 2.20859E-01 FCM(132)= 2.19538E-01 FCM(133)= 2.17952E-01 FCM(134)= 2.17154E-01 FCM(135)= 0.00000E+00 FCM(136)= 0.00000E+00 FCM(137)= 0.00000E+00 FCM(138)= 0.00000E+00 FCM(139)= 0.00000E+00 FCM(140)= 0.00000E+00 FCM(141)= 0.00000E+00 FCM(142)= 0.00000E+00 FCM(143)= 4.19601E-01 FCM(144)=-7.05109E-01 FCM(145)=-7.03743E-01 FCM(146)=-6.75253E-01 FCM(147)=-7.37080E-01 FCM(148)=-8.16210E-01 FCM(149)=-6.69546E-01 FCM(150)=-5.48247E-01 FCM(151)=-6.99334E-01 FCM(152)=-8.33513E-01 FCM(153)=-9.41013E-01 FCM(154)=-1.01917E+00 FCM(155)=-1.06672E+00 FCM(156)=-1.06672E+00 FCM(157)= 3.92273E-01 FCM(158)=-6.62278E-01 FCM(159)=-6.61139E-01 FCM(160)=-6.43922E-01 FCM(161)=-7.12552E-01 FCM(162)=-7.92288E-01 FCM(163)=-6.56454E-01 FCM(164)=-5.47945E-01 FCM(165)=-6.99334E-01 FCM(166)=-8.33513E-01 FCM(167)=-9.41013E-01 FCM(168)=-1.01917E+00 FCM(169)=-1.06672E+00 FCM(170)=-1.06672E+00 FCM(171)= 3.95453E-01 FCM(172)=-6.29118E-01 FCM(173)=-6.28157E-01 FCM(174)=-6.19876E-01 FCM(175)=-6.93930E-01 FCM(176)=-7.74230E-01 FCM(177)=-6.46571E-01 FCM(178)=-5.47717E-01 FCM(179)=-6.99334E-01 FCM(180)=-8.33513E-01 FCM(181)=-9.41013E-01 FCM(182)=-1.01917E+00 FCM(183)=-1.06672E+00 FCM(184)=-1.06672E+00 FCM(185)= 3.92438E-01 FCM(186)=-6.59217E-01 FCM(187)=-6.58102E-01 FCM(188)=-6.42080E-01 FCM(189)=-7.11494E-01 FCM(190)=-7.91451E-01 FCM(191)=-6.55996E-01 FCM(192)=-5.47935E-01 FCM(193)=-6.99334E-01 FCM(194)=-8.33513E-01 FCM(195)=-9.41013E-01 FCM(196)=-1.01917E+00 FCM(197)=-1.06672E+00 FCM(198)=-1.06672E+00 FCM(199)= 4.01378E-01 FCM(200)=-5.70890E-01 FCM(201)=-5.70227E-01 FCM(202)=-5.76716E-01 FCM(203)=-6.59595E-01 FCM(204)=-7.40466E-01 FCM(205)=-6.28093E-01 FCM(206)=-5.47290E-01 FCM(207)=-6.99334E-01 FCM(208)=-8.33513E-01 FCM(209)=-9.41013E-01 FCM(210)=-1.01917E+00 FCM(211)=-1.06672E+00 FCM(212)=-1.06672E+00 FCM(213)= 4.15875E-01 FCM(214)=-4.27880E-01 FCM(215)=-4.27949E-01 FCM(216)=-4.70817E-01 FCM(217)=-5.75448E-01 FCM(218)=-6.57769E-01 FCM(219)=-5.82836E-01 FCM(220)=-5.46245E-01 FCM(221)=-6.99334E-01 FCM(222)=-8.33513E-01 FCM(223)=-9.41013E-01 FCM(224)=-1.01917E+00 FCM(225)=-1.06672E+00 FCM(226)=-1.06672E+00 FCM(227)= 3.88070E-01 FCM(228)=-7.05109E-01 FCM(229)=-7.03743E-01 FCM(230)=-6.75253E-01 FCM(231)=-7.37080E-01 FCM(232)=-8.16210E-01 FCM(233)=-6.69546E-01 FCM(234)=-5.48247E-01 FCM(235)=-6.99334E-01 FCM(236)=-8.33513E-01 FCM(237)=-9.41013E-01 FCM(238)=-1.01917E+00 FCM(239)=-1.06672E+00 FCM(240)=-1.06672E+00 FCM(241)= 1.00000E-30 FCM(242)= 1.00000E-30 FCM(243)= 1.00000E-30 FCM(244)= 1.00000E-30 FCM(245)= 1.00000E-30 FCM(246)= 1.00000E-30 FCM(247)= 1.00000E-30 FCM(248)= 1.00000E-30 FCM(249)= 1.00000E-30 FCM(250)= 1.00000E-30 FCM(251)= 1.00000E-30 FCM(252)= 1.00000E-30 FCM(253)= 1.00000E-30 FCM(254)= 1.00000E-30 FCM(255)= 1.00000E-30 FCM(256)= 1.00000E-30 FCM(257)= 1.00000E-30 FCM(258)= 1.00000E-30 FCM(259)= 1.00000E-30 FCM(260)= 1.00000E-30 FCM(261)= 1.00000E-30 FCM(262)= 1.00000E-30 FCM(263)= 1.00000E-30 FCM(264)= 1.00000E-30 FCM(265)= 1.00000E-30 FCM(266)= 1.00000E-30 FCM(267)= 1.00000E-30 FCM(268)= 1.00000E-30 FCM(269)= 1.00000E-30 FCM(270)= 1.00000E-30 FCM(271)= 1.00000E-30 FCM(272)= 1.00000E-30 FCM(273)= 1.00000E-30 FCM(274)= 1.00000E-30 FCM(275)= 1.00000E-30 FCM(276)= 1.00000E-30 FCM(277)= 1.00000E-30 FCM(278)= 1.00000E-30 FCM(279)= 1.00000E-30 FCM(280)= 1.00000E-30 FCM(281)= 1.00000E-30 FCM(282)= 1.00000E-30 FCM(283)= 4.99862E-04 FCM(284)= 5.00121E-04 FCM(285)= 5.00157E-04 FCM(286)= 5.00199E-04 FCM(287)= 5.00248E-04 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS OF HIGH LIFT AND CONTROL DEVICES WING PLAIN TRAILING-EDGE FLAP CONFIGURATION PLAIN FLAPS ON WING, EXAMPLE PROBLEM 5, CASE 2 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 4.2600E+06 2.250 0.822 3.000 2.600 0.000 0 ---------INCREMENTS DUE TO DEFLECTION--------- ---DERIVATIVES (PER DEGREE)--- 0 DELTA D(CL) D(CM) D(CL MAX) D(CD MIN) (CLA)D (CH)A (CH)D 0.0 0.000 0.0000 0.000 0.00000 NDM -3.847E-03 -9.630E-03 10.0 0.079 -0.0418 0.083 0.00212 NDM -9.630E-03 20.0 0.138 -0.0707 0.144 0.00900 NDM -9.703E-03 30.0 0.160 -0.0842 0.192 0.01741 NDM -9.814E-03 40.0 0.189 -0.0916 0.220 0.02791 NDM -9.858E-03 60.0 0.238 -0.0997 0.253 0.05330 NDM -9.912E-03 0 *** NOTE * HINGE MOMENT DERIVATIVES ARE BASED ON TWICE THE AREA-MOMENT OF THE CONTROL ABOUT ITS HINGE LINE 0 --------- INDUCED DRAG COEFFICIENT INCREMENT , D(CDI) , DUE TO DEFLECTION --------- 0 DELTA = 0.0 10.0 20.0 30.0 40.0 60.0 ALPHA 0 -2.0 -1.40E-06 -7.13E-04 -3.59E-04 -3.10E-05 5.51E-04 1.97E-03 0.0 6.85E-10 6.85E-04 2.07E-03 2.79E-03 3.88E-03 6.16E-03 2.0 1.40E-06 2.08E-03 4.50E-03 5.61E-03 7.20E-03 1.03E-02 4.0 2.80E-06 3.48E-03 6.93E-03 8.43E-03 1.05E-02 1.45E-02 8.0 5.59E-06 6.27E-03 1.18E-02 1.41E-02 1.72E-02 2.29E-02 12.0 8.38E-06 9.07E-03 1.67E-02 1.97E-02 2.38E-02 3.13E-02 16.0 1.12E-05 1.19E-02 2.15E-02 2.54E-02 3.05E-02 3.97E-02 20.0 1.40E-05 1.47E-02 2.64E-02 3.10E-02 3.71E-02 4.81E-02 24.0 1.67E-05 1.75E-02 3.12E-02 3.66E-02 4.38E-02 5.65E-02 0***NDM PRINTED WHEN NO DATCOM METHODS EXIST 1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE. 0 $FLTCON NALPHA=9.0,ALSCHD=-2.0,0.0,2.0,4.0,8.0, 12.0,16.0,20.0,24.0$ $FLTCON NMACH=1.0,MACH(1)=0.60,RNNUB(1)=4.26E6,$ $OPTINS SREF=2.25,CBARR=0.822,BLREF=3.00$ $SYNTHS XCG=2.60,ZCG=0.0,XW=1.70,ZW=0.0,ALIW=0.0$ $BODY NX=10.0,BNOSE=2.0,BTAIL=1.0,BLN=1.46,BLA=1.97, X(1)=0.0,.175,.322,.530,.85,1.46,2.50,3.43,3.97,4.57, R(1)=0.0,.0417,.0833,.125,.1665,.208,.208,.208,.178,.138$ $WGPLNF CHRDTP=0.346,SSPNE=1.29,SSPN=1.50,CHRDR=1.16,SAVSI=45.0,CHSTAT=.25, TWISTA=0.0,SSPNDD=0.0,DHDADI=0.0,DHDADO=0.0,TYPE=1.0$ $WGSCHR TOVC=.060,DELTAY=1.30,XOVC=0.40,CLI=0.0,ALPHAI=0.0,CLALPA(1)=0.131, CLMAX(1)=.82,CM0=0.0,LERI=0.0025,CLAMO=.105,YCM=0.0$ $ASYFLP DELTAL(1)=5.,10.,20.,30.,40.,DELTAR(1)=-2.,-5.,-10.,-15.,-20., STYPE=4.0, NDELTA=5.,CHRDFI=.1116,CHRDFO=.0692,SPANFI=1.108,SPANFO=1.50,PHETE=.0522$ CASEID PLAIN FLAP AILERON, EXAMPLE PROBLEM 6, CASE 1 SAVE NEXT CASE 0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING-BODY CONFIGURATION PLAIN FLAP AILERON, EXAMPLE PROBLEM 6, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 4.2600E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.016 -0.125 0.0032 -0.126 0.012 -0.026 6.258E-02 -1.352E-03 -1.612E-03 -1.845E-03 5.509E-04 0.0 0.015 0.000 0.0000 0.000 0.015 ****** 6.258E-02 -1.864E-03 5.528E-12 2.0 0.016 0.125 -0.0042 0.126 0.012 -0.034 6.273E-02 -2.646E-03 -5.509E-04 4.0 0.024 0.251 -0.0106 0.252 0.006 -0.042 6.269E-02 -3.674E-03 -1.104E-03 8.0 0.067 0.500 -0.0293 0.505 -0.003 -0.058 6.082E-02 -4.565E-03 -2.201E-03 12.0 0.149 0.738 -0.0471 0.752 -0.007 -0.063 5.089E-02 -3.125E-03 -3.246E-03 16.0 0.236 0.907 -0.0543 0.937 -0.023 -0.058 3.176E-02 -1.423E-03 -3.993E-03 20.0 0.992 -0.0585 9.201E-03 -1.326E-04 -4.364E-03 24.0 0.981 -0.0554 -1.458E-02 1.698E-03 -4.317E-03 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS OF HIGH LIFT AND CONTROL DEVICES WING PLAIN TRAILING-EDGE FLAP CONFIGURATION PLAIN FLAP AILERON, EXAMPLE PROBLEM 6, CASE 1 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 4.2600E+06 2.250 0.822 3.000 2.600 0.000 0 ----------YAWING MOMENT COEFFICIENT,CN,DUE TO CONTROL DEFLECTION---------- 0(DELTAL-DELTAR)= 7.0 15.0 30.0 45.0 60.0 0ALPHA 0 -2.0 6.255E-05 1.340E-04 2.449E-04 3.116E-04 3.682E-04 0.0 0.000E+00 0.000E+00 0.000E+00 0.000E+00 0.000E+00 2.0 -6.255E-05 -1.340E-04 -2.449E-04 -3.116E-04 -3.682E-04 4.0 -1.253E-04 -2.685E-04 -4.905E-04 -6.242E-04 -7.376E-04 8.0 -2.493E-04 -5.342E-04 -9.758E-04 -1.242E-03 -1.467E-03 12.0 -3.677E-04 -7.879E-04 -1.439E-03 -1.832E-03 -2.164E-03 16.0 -4.544E-04 -9.737E-04 -1.779E-03 -2.264E-03 -2.675E-03 20.0 -4.987E-04 -1.069E-03 -1.952E-03 -2.484E-03 -2.935E-03 24.0 -4.923E-04 -1.055E-03 -1.927E-03 -2.452E-03 -2.898E-03 0 0 DELTAL DELTAR (CL)ROLL 0 5.0 -2.0 2.8724E-03 10.0 -5.0 6.1550E-03 20.0 -10.0 1.1244E-02 30.0 -15.0 1.4308E-02 40.0 -20.0 1.6907E-02 1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE. 0 $ASYFLP STYPE=3.0,DELTAD(1)=.0130,.0261,.0380,.0513,.0630,.0750, DELTAS(1)=.013,.0261,.038,.0513,.063,.075, XSOC(1)=.6980, .6955,.6880,.6638,.6456,.6250,XSPRME=.55,HSOC(1)=.0357,.0710,.0956,.1182, .1365,.1359$ CASEID SPOILER-SLOT-DEFLECTOR ON WING, EXAMPLE PROBLEM 6, CASE 2 NEXT CASE 0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING-BODY CONFIGURATION SPOILER-SLOT-DEFLECTOR ON WING, EXAMPLE PROBLEM 6, CASE 2 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 4.2600E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.016 -0.125 0.0032 -0.126 0.012 -0.026 6.258E-02 -1.352E-03 -1.612E-03 -1.845E-03 5.509E-04 0.0 0.015 0.000 0.0000 0.000 0.015 ****** 6.258E-02 -1.864E-03 5.528E-12 2.0 0.016 0.125 -0.0042 0.126 0.012 -0.034 6.273E-02 -2.646E-03 -5.509E-04 4.0 0.024 0.251 -0.0106 0.252 0.006 -0.042 6.269E-02 -3.674E-03 -1.104E-03 8.0 0.067 0.500 -0.0293 0.505 -0.003 -0.058 6.082E-02 -4.565E-03 -2.201E-03 12.0 0.149 0.738 -0.0471 0.752 -0.007 -0.063 5.089E-02 -3.125E-03 -3.246E-03 16.0 0.236 0.907 -0.0543 0.937 -0.023 -0.058 3.176E-02 -1.423E-03 -3.993E-03 20.0 0.992 -0.0585 9.201E-03 -1.326E-04 -4.364E-03 24.0 0.981 -0.0554 -1.458E-02 1.698E-03 -4.317E-03 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS OF HIGH LIFT AND CONTROL DEVICES WING WITH SPOILER-SLOT-DEFLECTOR CONFIGURATION SPOILER-SLOT-DEFLECTOR ON WING, EXAMPLE PROBLEM 6, CASE 2 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 4.2600E+06 2.250 0.822 3.000 2.600 0.000 0 XS/C HS/C DD/C DS/C (CL)ROLL CN 0 0.6980 0.0357 0.0130 0.0130 1.4718E-03 8.395E-04 0.6955 0.0710 0.0261 0.0261 2.0021E-03 1.685E-03 0.6880 0.0956 0.0380 0.0380 2.9778E-03 2.454E-03 0.6638 0.1182 0.0513 0.0513 3.6314E-03 3.313E-03 0.6456 0.1365 0.0630 0.0630 4.0488E-03 4.068E-03 1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE. 0 $FLTCON NMACH=1.0,MACH(1)=.60,NALPHA=9.0,ALSCHD(1)=-2.0,0.0,2.0,4.0,8.0, 12.0,16.0,20.0,24.0,RNNUB(1)=2.28E6$ $OPTINS SREF=2.25,CBARR=0.822,BLREF=3.0$ $SYNTHS XCG=2.60,ZCG=0.0,XW=1.70,ZW=0.0,ALIW=0.0,XH=3.93,ZH=0.0,ALIH=0.0, XV=3.34,VERTUP=.TRUE.$ $BODY NX=10., X(1)=0.0,.175,.322,.530,.85,1.46,2.50,3.43,3.97,4.57, R(1)=0.0,.0417,.0833,.125,.1665,.208,.208,.208,.178,.138$ $WGPLNF CHRDTP=0.346,SSPNE=1.29,SSPN=1.50,CHRDR=1.16,SAVSI=45.0,CHSTAT=.25, TWISTA=0.0,SSPNDD=0.0,DHDADI=0.0,DHDADO=0.0,TYPE=1.0$ $WGSCHR TOVC=.060,DELTAY=1.30,XOVC=0.40,CLI=0.0,ALPHAI=0.0,CLALPA(1)=0.131, CLMAX(1)=.82,CM0=0.0,LERI=0.0025,CLAMO=.105,YCM=0.0$ $WGSCHR CLMAXL=0.78$ $VTPLNF CHRDTP=.420,SSPNE=.63,SSPN=.849,CHRDR=1.02,SAVSI=28.1, CHSTAT=.25,TWISTA=0.0,TYPE=1.0$ $VTSCHR TOVC=.09,XOVC=0.40,CLALPA(1)=0.141,LERI=.0075$ $HTPLNF CHRDTP=.253,SSPNE=.52,SSPN=.67,CHRDR=.42,SAVSI=45.0,CHSTAT=0.25, TWISTA=0.0,SSPNDD=0.0,DHDADI=0.0,DHDADO=0.0,TYPE=1.0$ $HTSCHR TOVC=0.060,DELTAY=1.30,XOVC=0.40,CLI=0.0,ALPHAI=0.0,CLALPA(1)=.131, CLMAX(1)=0.82,CMO=0.0,LERI=.0025,CLAMO=.105,YCM=0.0$ $SYMFLP FTYPE=1.0,NDELTA=9.,DELTA(1)=-60.,-40.,-20.,-10.,0.,10., 20.,40.,60.,PHETE=.0522,PHETEP=.0523,SPANFI=.18,SPANFO=.670,CHRDFI=.075, CHRDFO=.051,CB=.0038,TC=.0076,NTYPE=1.0,$ $EXPR01 CLWB(1)=.09,.204,.330,.450,.690,.895,1.070,1.180,1.174$ TRIM CASEID INCLUDES HIGH LIFT EFFECT ON WING, EXAMPLE PROBLEM 7 NEXT CASE 0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION INCLUDES HIGH LIFT EFFECT ON WING, EXAMPLE PROBLEM 7 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 2.2800E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.021 0.081 0.0227 0.081 0.024 0.282 5.835E-02 -1.108E-02 -1.601E-02 4.017E-03 -2.307E-03 0.0 0.019 0.204 0.0000 0.204 0.019 0.000 6.434E-02 -1.162E-02 -2.652E-03 2.0 0.021 0.339 -0.0238 0.339 0.009 -0.070 6.626E-02 -1.335E-02 -3.049E-03 4.0 0.030 0.469 -0.0534 0.470 -0.003 -0.114 6.532E-02 -1.567E-02 -3.417E-03 8.0 0.077 0.731 -0.1229 0.735 -0.025 -0.167 6.157E-02 -1.819E-02 -4.150E-03 12.0 0.163 0.962 -0.1989 0.974 -0.041 -0.204 5.470E-02 -1.988E-02 -4.719E-03 16.0 0.258 1.169 -0.2819 1.195 -0.074 -0.236 4.442E-02 -2.220E-02 -5.133E-03 20.0 1.317 -0.3765 2.147E-02 -2.024E-02 -5.234E-03 24.0 1.341 -0.4439 -9.573E-03 -1.345E-02 -4.812E-03 0 ALPHA Q/QINF EPSLON D(EPSLON)/D(ALPHA) 0 -2.0 0.937 -1.234 0.617 0.0 0.904 0.000 0.617 2.0 0.937 1.234 0.603 4.0 0.991 2.413 0.572 8.0 1.000 4.565 0.493 12.0 1.000 6.358 0.359 16.0 1.000 7.435 0.152 20.0 1.000 7.576 -0.084 24.0 1.000 6.766 -0.202 0*NOTE* OUTPUT REFLECTS EXPERIMENTAL DATA INPUTS 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS OF HIGH LIFT AND CONTROL DEVICES TAIL PLAIN TRAILING-EDGE FLAP CONFIGURATION INCLUDES HIGH LIFT EFFECT ON WING, EXAMPLE PROBLEM 7 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 2.2800E+06 2.250 0.822 3.000 2.600 0.000 0 ---------INCREMENTS DUE TO DEFLECTION--------- ---DERIVATIVES (PER DEGREE)--- 0 DELTA D(CL) D(CM) D(CL MAX) D(CD MIN) (CLA)D (CH)A (CH)D -60.0 -0.058 0.1177 0.086 0.01369 NDM -1.722E-03 -8.476E-03 -40.0 -0.046 0.0957 0.075 0.00698 NDM -8.398E-03 -20.0 -0.034 0.0704 0.049 0.00202 NDM -8.172E-03 -10.0 -0.019 0.0406 0.028 0.00042 NDM -8.066E-03 0.0 0.000 0.0000 0.000 0.00000 NDM -8.066E-03 10.0 0.019 -0.0406 0.028 0.00042 NDM -8.066E-03 20.0 0.034 -0.0704 0.049 0.00202 NDM -8.172E-03 40.0 0.046 -0.0957 0.075 0.00698 NDM -8.398E-03 60.0 0.058 -0.1191 0.086 0.01369 NDM -8.476E-03 0 *** NOTE * HINGE MOMENT DERIVATIVES ARE BASED ON TWICE THE AREA-MOMENT OF THE CONTROL ABOUT ITS HINGE LINE 0 --------- INDUCED DRAG COEFFICIENT INCREMENT , D(CDI) , DUE TO DEFLECTION --------- 0 DELTA = -60.0 -40.0 -20.0 -10.0 0.0 10.0 20.0 40.0 60.0 ALPHA 0 -2.0 2.72E-03 1.78E-03 1.02E-03 3.98E-04 -1.42E-07 1.13E-04 5.25E-04 1.11E-03 1.87E-03 0.0 2.30E-03 1.44E-03 7.72E-04 2.55E-04 2.55E-10 2.55E-04 7.72E-04 1.44E-03 2.30E-03 2.0 1.87E-03 1.11E-03 5.25E-04 1.13E-04 1.43E-07 3.98E-04 1.02E-03 1.78E-03 2.72E-03 4.0 1.41E-03 7.42E-04 2.59E-04 -3.99E-05 2.95E-07 5.51E-04 1.29E-03 2.15E-03 3.18E-03 8.0 3.80E-04 -7.49E-05 -3.39E-04 -3.83E-04 6.39E-07 8.94E-04 1.88E-03 2.96E-03 4.21E-03 12.0 -8.51E-04 -1.05E-03 -1.05E-03 -7.94E-04 1.05E-06 1.30E-03 2.60E-03 3.94E-03 5.44E-03 16.0 -2.48E-03 -2.34E-03 -2.00E-03 -1.34E-03 1.59E-06 1.85E-03 3.54E-03 5.23E-03 7.07E-03 20.0 -4.63E-03 -4.05E-03 -3.25E-03 -2.06E-03 2.31E-06 2.57E-03 4.79E-03 6.94E-03 9.22E-03 24.0 -7.31E-03 -6.18E-03 -4.80E-03 -2.95E-03 3.21E-06 3.46E-03 6.35E-03 9.07E-03 1.19E-02 0***NDM PRINTED WHEN NO DATCOM METHODS EXIST 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS OF HIGH LIFT AND CONTROL DEVICES WING-BODY-TAIL TRIM WITH CONTROL DEVICE ON TAIL ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 2.2800E+06 2.250 0.822 3.000 2.600 0.000 0 ----------UNTRIMMED---------- -----------------------AT TRIM DEFLECTION----------------------- 0 ALPHA CL CD CM DELTAT D(CL) D(CL MAX) D(CDI) D(CD MIN) CH(A) CH(D) 0 -2.0 0.081 0.021 0.0227 5.6 0.011 0.016 6.31E-05 0.00024 -1.722E-03 -8.066E-03 0.0 0.204 0.019 0.0000 0.0 0.000 0.000 2.56E-07 0.00000 -8.066E-03 2.0 0.339 0.021 -0.0238 -5.9 -0.011 0.017 6.62E-05 0.00025 -8.066E-03 4.0 0.469 0.030 -0.0534 -14.3 -0.026 0.037 8.86E-05 0.00111 -8.111E-03 0*NOTE** TRIM RESULTS HAVE BEEN TERMINATED DUE TO LACK OF CONTROL MOMENT. 1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE. 0 $FLTCON NMACH=1.0,MACH(1)=0.60,NALPHA=9.0,ALSCHD(1)=-2.0,0.0,2.0,4.0,8.0, 12.0,16.0,20.0,24.0,RNNUB(1)=2.28E6$ $OPTINS SREF=2.25,CBARR=0.822,BLREF=3.00$ $SYNTHS XCG=2.60,ZCG=0.0,XW=1.70,ZW=0.0,ALIW=0.0,XH=3.93,ZH=0.0,ALIH=0.0, XV=3.34,VERTUP=.TRUE.$ $SYNTHS HINAX=4.271$ $BODY NX=10.0, X(1)=0.0,.175,.322,.530,.85,1.46,2.50,3.43,3.97,4.57, R(1)=0.0,.0417,.0833,.125,.1655,.208,.208,.208,.178,.138$ $WGPLNF CHRDTP=0.346,SSPNE=1.29,SSPN=1.50,CHRDR=1.16,SAVSI=45.0,CHSTAT=.25, TWISTA=0.0,SSPNDD=0.0,DHDADI=0.0,DHDADO=0.0,TYPE=1.0$ $WGSCHR TOVC=.060,DELTAY=1.30,XOVC=0.40,CLI=0.0,ALPHAI=0.0,CLALPA(1)=0.131, CLMAX(1)=.82,CM0=0.0,LERI=0.0025,CLAMO=.105,YCM=0.0$ $WGSCHR CLMAXL=0.78$ $VTPLNF CHRDTP=.420,SSPNE=.63,SSPN=.849,CHRDR=1.02,SAVSI=28.1, CHSTAT=.25,TWISTA=0.0,TYPE=1.0$ $VTSCHR TOVC=.09,XOVC=0.04,CLALPA(1)=0.141,LERI=.0075$ $HTPLNF CHRDTP=.253,SSPNE=.52,SSPN=.67,CHRDR=.42,SAVSI=45.0,CHSTAT=0.25, TWISTA=0.0,SSPNDD=0.0,DHDADI=0.0,DHDADO=0.0,TYPE=1.0$ $HTSCHR TOVC=0.060,DELTAY=1.30,XOVC=0.40,CLI=0.0,ALPHAI=0.0,CLALPA(1)=.131, CLMAX(1)=0.82,CMO=0.0,LERI=.0025,CLAMO=.105,YCM=0.0$ CASEID ALL MOVEABLE HORIZONTAL TAIL, EXAMPLE PROBLEM 8 TRIM NEXT CASE 0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION ALL MOVEABLE HORIZONTAL TAIL, EXAMPLE PROBLEM 8 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 2.2800E+06 2.250 0.822 3.000 2.600 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -2.0 0.021 -0.134 0.0228 -0.135 0.016 -0.169 6.693E-02 -1.109E-02 -1.601E-02 4.022E-03 -1.360E-03 0.0 0.019 0.000 0.0000 0.000 0.019 ****** 6.693E-02 -1.163E-02 -1.755E-03 2.0 0.021 0.134 -0.0238 0.135 0.016 -0.177 6.749E-02 -1.335E-02 -2.147E-03 4.0 0.030 0.270 -0.0534 0.271 0.011 -0.197 6.801E-02 -1.568E-02 -2.541E-03 8.0 0.077 0.542 -0.1230 0.547 0.001 -0.225 6.677E-02 -1.820E-02 -3.315E-03 12.0 0.163 0.804 -0.1990 0.820 -0.008 -0.243 5.809E-02 -1.989E-02 -4.026E-03 16.0 0.259 1.006 -0.2821 1.039 -0.029 -0.272 4.056E-02 -2.221E-02 -4.417E-03 20.0 1.129 -0.3766 1.767E-02 -2.025E-02 -4.405E-03 24.0 1.148 -0.4441 -8.151E-03 -1.346E-02 -3.962E-03 0 ALPHA Q/QINF EPSLON D(EPSLON)/D(ALPHA) 0 -2.0 0.937 -1.234 0.617 0.0 0.904 0.000 0.617 2.0 0.937 1.234 0.603 4.0 0.991 2.413 0.572 8.0 1.000 4.565 0.493 12.0 1.000 6.358 0.359 16.0 1.000 7.435 0.152 20.0 1.000 7.576 -0.084 24.0 1.000 6.766 -0.202 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS OF HIGH LIFT AND CONTROL DEVICES WING-BODY-VERTICAL TAIL-ALL MOVABLE HORIZONTAL STABILIZER TRIM CONFIGURATION ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.600 2.2800E+06 2.250 0.822 3.000 2.600 0.000 0-----------------UNTRIMMED--------------------HORIZONTAL STABILIZER COEFFICIENTS----------------AT TRIM INCIDENCE------------ 0 ALPHA CD CL CM HM ALIHT CD CL CM HM -2.0 0.002 -0.016 0.0358 3.195E-03 1.1 0.001 0.001 -0.0034 -2.881E-04 0.0 0.002 0.000 0.0000 0.000E+00 0.0 0.001 0.000 0.0000 0.000E+00 2.0 0.002 0.016 -0.0356 -3.195E-03 -1.2 0.001 -0.002 0.0044 3.794E-04 4.0 0.004 0.032 -0.0721 -6.461E-03 -2.5 0.001 -0.005 0.0109 9.460E-04 8.0 0.011 0.065 -0.1471 -1.314E-02 -5.7 0.001 -0.013 0.0299 2.614E-03 12.0 0.021 0.096 -0.2177 -1.953E-02 -9.4 0.000 -0.022 0.0478 4.198E-03 16.0 0.032 0.119 -0.2735 -2.447E-02 -14.2 -0.001 -0.025 0.0550 4.834E-03 20.0 0.038 0.132 -0.3107 -2.729E-02 -24.1 -0.001 -0.027 0.0594 5.204E-03 24.0 0.043 0.140 -0.3400 -2.886E-02 -58.4 -0.001 -0.027 0.0569 4.927E-03 0 WING-BODY-TAIL COEFFICIENTS AT TRIM INCIDENCE 0 ALPHA CD CL 0 -2.0 0.021 -0.124 0.0 0.019 0.000 2.0 0.021 0.123 4.0 0.029 0.246 8.0 0.072 0.486 12.0 0.151 0.713 16.0 0.237 0.876 20.0 0.001 0.952 24.0 0.001 0.935 0*NOTE** ANGLES OF ATTACK WHERE NO OUTPUT EXISTS INDICATES LACK OF CONTROL MOMENT 1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE. 0 $FLTCON NMACH=1.0,MACH(1)=.26,NALPHA=6.0,ALSCHD(1)=-5.0,0.0,5.0,10.0,15.0, 20.0,RNNUB(1)=1.86E6$ $LARWB ZB=0.0,SREF=.989,DELTEP=90.0,SFRONT=.307,AR=1.076,L=1.915,SWET=2.28, PERBAS=2.38,SBASE=0.307,HB=.595,BB=1.03,BLF=.FALSE.,XCG=1.44,THETAD=15.0, ROUNDN=.FALSE.,SBS=.57,SBSLB=.0228,XCENSB=1.277,XCENW=1.277$ CASEID LIFTING BODY WITH SHARP LEADING EDGE, EXAMPLE PROBLEM 9 NEXT CASE 0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP LOW ASPECT RATIO WINGS AND WING-BODY COMBINATIONS LIFTING BODY WITH SHARP LEADING EDGE, EXAMPLE PROBLEM 9 ----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------ MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER NUMBER NUMBER AREA LONG. LAT. HORIZ VERT FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT 0 0.260 1.8600E+06 0.989 1.915 NA 1.440 0.000 0 -------------------DERIVATIVE (PER DEGREE)------------------- 0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB 0 -5.0 0.097 -0.103 -0.0133 -0.111 0.088 0.120 1.802E-02 2.371E-03 -8.248E-03 -2.084E-05 1.153E-03 0.0 0.081 0.000 0.0000 0.000 0.081 ****** 2.311E-02 2.966E-03 -8.691E-03 -2.168E-05 0.000E+00 5.0 0.089 0.128 0.0163 0.136 0.078 0.120 2.795E-02 3.567E-03 -8.029E-03 -2.042E-05 -1.410E-03 10.0 0.122 0.279 0.0357 0.296 0.072 0.120 3.217E-02 4.181E-03 -5.526E-03 -1.567E-05 -2.585E-03 15.0 0.188 0.450 0.0581 0.483 0.065 0.120 3.558E-02 4.810E-03 -2.847E-04 -5.733E-06 -2.860E-03 20.0 0.290 0.635 0.0838 0.696 0.056 0.120 3.854E-02 5.445E-03 8.765E-03 1.143E-05 -1.392E-03 1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE. 0 $FLTCON MACH(1)=10.0,NMACH=1.0,RNNUB(1)=1.E7,PINF(1)=10.,HYPERS=.TRUE.$ $TRNJET TIME(1)=1.,2.,3.,4.,5.,FC(1)=1000.,2000.,1000.,500.,200.,NT=5., ALPHA(1)=0.,3.,6.,9.,13.,LAMNRJ(1)=.FALSE.,.FALSE.,.FALSE.,.FALSE., .TRUE.,ME=2.39,ISP=225.,SPAN=2.0,PHE=30.,GP=1.2,CC=90.,LFP=10.$ CASEID TRANSVERSE-JET SIZING, EXAMPLE PROBLEM 10 DUMP JET NEXT CASE 0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000 IOM( 1)= 1.01000E+01 IOM( 2)= 9.02163E+00 IOM( 3)= 8.00683E+00 IOM( 4)= 6.99487E+00 IOM( 5)= 5.90500E+00 IOM( 6)= 1.00000E-30 IOM( 7)= 1.00000E-30 IOM( 8)= 1.00000E-30 IOM( 9)= 1.00000E-30 IOM( 10)= 1.00000E-30 IOM( 11)= 1.01663E+08 IOM( 12)= 1.42167E+08 IOM( 13)= 1.75408E+08 IOM( 14)= 1.90843E+08 IOM( 15)= 1.87500E+08 IOM( 16)= 1.00000E-30 IOM( 17)= 1.00000E-30 IOM( 18)= 1.00000E-30 IOM( 19)= 1.00000E-30 IOM( 20)= 1.00000E-30 IOM( 21)= 1.38000E+01 IOM( 22)= 2.08101E+01 IOM( 23)= 4.07188E+01 IOM( 24)= 6.27000E+01 IOM( 25)= 1.09368E+02 IOM( 26)= 1.00000E-30 IOM( 27)= 1.00000E-30 IOM( 28)= 1.00000E-30 IOM( 29)= 1.00000E-30 IOM( 30)= 1.00000E-30 IOM( 31)= 7.07000E+02 IOM( 32)= 1.12617E+03 IOM( 33)= 1.61844E+03 IOM( 34)= 2.03869E+03 IOM( 35)= 2.48640E+03 IOM( 36)= 1.00000E-30 IOM( 37)= 1.00000E-30 IOM( 38)= 1.00000E-30 IOM( 39)= 1.00000E-30 IOM( 40)= 1.00000E-30 IOM( 41)= 4.91121E-04 IOM( 42)= 6.16641E-04 IOM( 43)= 2.14542E-04 IOM( 44)= 8.51582E-05 IOM( 45)= 2.79297E-05 IOM( 46)= 1.00000E-30 IOM( 47)= 1.00000E-30 IOM( 48)= 1.00000E-30 IOM( 49)= 1.00000E-30 IOM( 50)= 1.00000E-30 IOM( 51)= 5.01465E-04 IOM( 52)= 6.29630E-04 IOM( 53)= 2.19061E-04 IOM( 54)= 8.69520E-05 IOM( 55)= 2.85180E-05 IOM( 56)= 1.00000E-30 IOM( 57)= 1.00000E-30 IOM( 58)= 1.00000E-30 IOM( 59)= 1.00000E-30 IOM( 60)= 1.00000E-30 IOM( 61)= 2.83407E+00 IOM( 62)= 2.79993E+00 IOM( 63)= 2.82287E+00 IOM( 64)= 2.79974E+00 IOM( 65)= 6.08532E+00 IOM( 66)= 1.00000E-30 IOM( 67)= 1.00000E-30 IOM( 68)= 1.00000E-30 IOM( 69)= 1.00000E-30 IOM( 70)= 1.00000E-30 IOM( 71)= 3.91680E+00 IOM( 72)= 3.86405E+00 IOM( 73)= 3.89949E+00 IOM( 74)= 3.86376E+00 IOM( 75)= 8.94124E+00 IOM( 76)= 1.00000E-30 IOM( 77)= 1.00000E-30 IOM( 78)= 1.00000E-30 IOM( 79)= 1.00000E-30 IOM( 80)= 1.00000E-30 IOM( 81)= 2.55310E+02 IOM( 82)= 5.17592E+02 IOM( 83)= 2.56444E+02 IOM( 84)= 1.29408E+02 IOM( 85)= 2.23683E+01 IOM( 86)= 1.00000E-30 IOM( 87)= 1.00000E-30 IOM( 88)= 1.00000E-30 IOM( 89)= 1.00000E-30 IOM( 90)= 1.00000E-30 IOM( 91)= 5.76850E+02 IOM( 92)= 5.26038E+02 IOM( 93)= 4.77000E+02 IOM( 94)= 4.26241E+02 IOM( 95)= 3.71535E+02 IOM( 96)= 1.00000E-30 IOM( 97)= 1.00000E-30 IOM( 98)= 1.00000E-30 IOM( 99)= 1.00000E-30 IOM(100)= 1.00000E-30 IOM(101)= 7.96053E+03 IOM(102)= 1.09469E+04 IOM(103)= 1.94229E+04 IOM(104)= 2.67253E+04 IOM(105)= 4.06342E+04 IOM(106)= 1.00000E-30 IOM(107)= 1.00000E-30 IOM(108)= 1.00000E-30 IOM(109)= 1.00000E-30 IOM(110)= 1.00000E-30 IOM(111)= 2.00435E+04 IOM(112)= 4.06342E+04 IOM(113)= 2.01325E+04 IOM(114)= 1.01593E+04 IOM(115)= 1.75605E+03 IOM(116)= 1.00000E-30 IOM(117)= 1.00000E-30 IOM(118)= 1.00000E-30 IOM(119)= 1.00000E-30 IOM(120)= 1.00000E-30 IOM(121)= 1.13471E+00 IOM(122)= 2.30041E+00 IOM(123)= 1.13975E+00 IOM(124)= 5.75146E-01 IOM(125)= 9.94145E-02 IOM(126)= 1.00000E-30 IOM(127)= 1.00000E-30 IOM(128)= 1.00000E-30 IOM(129)= 1.00000E-30 IOM(130)= 1.00000E-30 IOM(131)= 0.00000E+00 IOM(132)= 1.71756E+00 IOM(133)= 3.43764E+00 IOM(134)= 4.29509E+00 IOM(135)= 4.63237E+00 IOM(136)= 1.00000E-30 IOM(137)= 1.00000E-30 IOM(138)= 9.98682E-01 IOM(139)= 9.98436E-01 IOM(140)= 9.99481E-01 IOM(141)= 9.99808E-01 IOM(142)= 9.98700E-01 IOM(143)= 1.00000E-30 IOM(144)= 1.00000E-30 IOM(145)= 1.00000E-30 IOM(146)= 1.00000E-30 IOM(147)= 1.00000E-30 IOM(148)= 1.00000E-30 IOM(149)= 1.00000E-30 IOM(150)= 1.00000E-30 IOM(151)= 1.00000E-30 IOM(152)= 1.00000E-30 IOM(153)= 1.00000E-30 IOM(154)= 1.00000E-30 IOM(155)= 1.00000E-30 IOM(156)= 1.00000E-30 IOM(157)= 1.00000E-30 IOM(158)= 1.00000E-30 IOM(159)= 1.00000E-30 IOM(160)= 1.00000E-30 IOM(161)= 1.00000E-30 IOM(162)= 1.00000E-30 IOM(163)= 1.00000E-30 IOM(164)= 1.00000E-30 IOM(165)= 1.00000E-30 IOM(166)= 1.00000E-30 IOM(167)= 1.00000E-30 IOM(168)= 1.00000E-30 IOM(169)= 1.00000E-30 IOM(170)= 1.00000E-30 IOM(171)= 1.00000E-30 IOM(172)= 1.00000E-30 IOM(173)= 1.00000E-30 IOM(174)= 1.00000E-30 IOM(175)= 1.00000E-30 IOM(176)= 1.00000E-30 IOM(177)= 1.00000E-30 IOM(178)= 1.00000E-30 IOM(179)= 1.00000E-30 IOM(180)= 1.00000E-30 IOM(181)= 1.00000E-30 IOM(182)= 1.00000E-30 IOM(183)= 1.00000E-30 IOM(184)= 1.00000E-30 IOM(185)= 1.00000E-30 IOM(186)= 1.00000E-30 IOM(187)= 1.00000E-30 IOM(188)= 1.00000E-30 IOM(189)= 1.00000E-30 IOM(190)= 1.00000E-30 IOM(191)= 1.00000E-30 IOM(192)= 1.00000E-30 IOM(193)= 1.00000E-30 IOM(194)= 1.00000E-30 IOM(195)= 1.00000E-30 IOM(196)= 1.00000E-30 IOM(197)= 1.00000E-30 IOM(198)= 1.00000E-30 IOM(199)= 1.00000E-30 IOM(200)= 1.00000E-30 JET( 1)= 7.00000E+02 JET( 2)= 1.24184E+00 JET( 3)= 1.99976E+00 JET( 4)= 5.17592E+02 JET( 5)= 4.06342E+04 JET( 6)= 4.74871E-06 JET( 7)= 1.00000E-30 JET( 8)= 1.00000E-30 JET( 9)= 1.00000E-30 JET( 10)= 1.00000E-30 JET( 11)= 1.00000E-30 JET( 12)= 1.00000E-30 JET( 13)= 1.00000E-30 JET( 14)= 1.00000E-30 JET( 15)= 1.00000E-30 JET( 16)= 1.00000E-30 JET( 17)= 3.91680E+00 JET( 18)= 3.86405E+00 JET( 19)= 3.89949E+00 JET( 20)= 3.86376E+00 JET( 21)= 8.94124E+00 JET( 22)= 1.00000E-30 JET( 23)= 1.00000E-30 JET( 24)= 1.00000E-30 JET( 25)= 1.00000E-30 JET( 26)= 1.00000E-30 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM SPECIAL CONTROL METHODS TRANSVERSE-JET CONTROL EFFECTIVENESS TRANSVERSE-JET SIZING, EXAMPLE PROBLEM 10 0 TIME (SEC) 1.0 2.0 3.0 4.0 5.0 0 CONTROL FORCE (LB) 0.100E+04 0.200E+04 0.100E+04 0.500E+03 0.200E+03 0 LOCAL MACH NO. 10.1 9.0 8.0 7.0 5.9 0 REYNOLDS NO. 0.102E+09 0.142E+09 0.175E+09 0.191E+09 0.187E+09 0 LOCAL PRESSURE (LB/IN2) 0.138E+02 0.208E+02 0.407E+02 0.627E+02 0.109E+03 0 DYNAMIC PRESSURE (LB/IN2) 0.707E+03 0.113E+04 0.162E+04 0.204E+04 0.249E+04 0 BOUNDARY LAYER TURB TURB TURB TURB LAM 0 CONTROL-FORCE COEFF. 0.491E-03 0.617E-03 0.215E-03 0.852E-04 0.279E-04 0 CORRECTED FORCE COEFF. 0.501E-03 0.630E-03 0.219E-03 0.870E-04 0.285E-04 0 SONIC AMPLIFICATION FACTOR 2.83 2.80 2.82 2.80 6.09 0 AMPLIFICATION FACTOR 3.9 3.9 3.9 3.9 8.9 0 VACUUM THRUST (LB) 0.255E+03 0.518E+03 0.256E+03 0.129E+03 0.224E+02 0 MIN. PRESSURE RATIO 0.577E+03 0.526E+03 0.477E+03 0.426E+03 0.372E+03 0 MIN. JET PRESSURE (LB/IN2) 0.796E+04 0.109E+05 0.194E+05 0.267E+05 0.406E+05 0 JET PRESSURE (LB/IN2) 0.200E+05 0.406E+05 0.201E+05 0.102E+05 0.176E+04 0 MASS-FLOW RATE (LB/SEC) 1.13 2.30 1.14 0.58 0.10 0 PROPELLANT WEIGHT (LB) 0.00 1.72 3.44 4.30 4.63 1 1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE. 0 $FLTCON NMACH=1.,MACH(1)=10.,NALPHA=5.,ALSCHD(1)=0.,5.,10.,15.,20., RNNUB(1)=1.06E5,HYPERS=.TRUE.$ $OPTINS SREF=1.,CBARR=1.$ $HYPEFF ALITD=150000.,XHL=8.,TWOTI=3.122,CF=2.0,HDELTA(1)=0.,2.,4.,6., 10.,12.,16.,20.,25.,30.,LAMNR=.TRUE.,HNDLTA=10.$ CASEID FLAT PLATE WITH FLAP IN HYPERSONIC FLOW, EXAMPLE PROBLEM 11 NEXT CASE 0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM AERODYNAMIC CONTROL EFFECTIVENESS AT HYPERSONIC SPEEDS FLAT PLATE WITH FLAP IN HYPERSONIC FLOW, EXAMPLE PROBLEM 11 MACH NUMBER=10.00 REYNOLDS NO./FT= 0.11E+06 0 REF. AREA (FT2)= 1.000 MOMENT REFERENCE CENTER = HL LONG. REF. LENGTH(FT)= 1.000 0 ----------INCREMENT IN NORMAL FORCE PER SPANWISE FOOT OF CONTROL---------- 0 DELTA = 0.0 2.0 4.0 6.0 10.0 12.0 16.0 20.0 25.0 30.0 ALPHA 0 0.0 0.00E+00 0.24E-01 0.52E-01 0.84E-01 0.15E+00 0.17E+00 0.22E+00 0.26E+00 0.30E+00 0.33E+00 5.0 0.00E+00 0.39E-01 0.60E-01 0.84E-01 0.13E+00 0.15E+00 0.19E+00 0.23E+00 0.27E+00 0.30E+00 10.0 0.00E+00 0.76E-01 0.17E+00 0.26E+00 0.49E+00 0.64E+00 0.10E+01 0.14E+01 0.21E+01 0.28E+01 15.0 0.00E+00 0.12E+00 0.26E+00 0.40E+00 0.78E+00 0.10E+01 0.16E+01 0.24E+01 0.36E+01 0.51E+01 20.0 0.00E+00 0.15E+00 0.33E+00 0.52E+00 0.99E+00 0.13E+01 0.20E+01 0.28E+01 0.41E+01 0.57E+01 0 ----------INCREMENT IN AXIAL FORCE PER SPANWISE FOOT OF CONTROL---------- 0 DELTA = 0.0 2.0 4.0 6.0 10.0 12.0 16.0 20.0 25.0 30.0 ALPHA 0 0.0 0.00E+00 0.84E-03 0.42E-03 0.15E-02 0.53E-02 0.77E-02 0.13E-01 0.19E-01 0.25E-01 0.31E-01 5.0 0.00E+00 0.14E-02 0.13E-02 0.24E-02 0.52E-02 0.69E-02 0.11E-01 0.15E-01 0.20E-01 0.25E-01 10.0 0.00E+00 0.26E-02 0.64E-02 0.18E-01 0.72E-01 0.12E+00 0.26E+00 0.50E+00 0.94E+00 0.16E+01 15.0 0.00E+00 0.41E-02 0.13E-01 0.34E-01 0.12E+00 0.20E+00 0.45E+00 0.85E+00 0.17E+01 0.29E+01 20.0 0.00E+00 0.53E-02 0.18E-01 0.47E-01 0.16E+00 0.26E+00 0.55E+00 0.10E+01 0.19E+01 0.32E+01 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM AERODYNAMIC CONTROL EFFECTIVENESS AT HYPERSONIC SPEEDS FLAT PLATE WITH FLAP IN HYPERSONIC FLOW, EXAMPLE PROBLEM 11 MACH NUMBER=10.00 REYNOLDS NO./FT= 0.11E+06 0 REF. AREA (FT2)= 1.000 MOMENT REFERENCE CENTER = HL LONG. REF. LENGTH(FT)= 1.000 0 ----------INCREMENT IN PITCHING MOMENT DUE TO NORMAL FORCE INCREMENT PER SPANWISE FOOT OF CONTROL---------- 0 DELTA = 0.0 2.0 4.0 6.0 10.0 12.0 16.0 20.0 25.0 30.0 ALPHA 0 0.0 0.00E+00 -0.24E-01 0.18E+00 0.27E+00 0.43E+00 0.51E+00 0.67E+00 0.80E+00 0.95E+00 0.11E+01 5.0 0.00E+00 -0.39E-01 0.14E+00 0.22E+00 0.37E+00 0.45E+00 0.59E+00 0.72E+00 0.86E+00 0.98E+00 10.0 0.00E+00 -0.76E-01 0.83E-02 -0.15E+00 -0.46E+00 -0.64E+00 -0.11E+01 -0.15E+01 -0.22E+01 -0.28E+01 15.0 0.00E+00 -0.12E+00 -0.16E+00 -0.35E+00 -0.80E+00 -0.11E+01 -0.17E+01 -0.25E+01 -0.37E+01 -0.50E+01 20.0 0.00E+00 -0.15E+00 -0.27E+00 -0.49E+00 -0.10E+01 -0.13E+01 -0.21E+01 -0.29E+01 -0.41E+01 -0.54E+01 0 ----------INCREMENT IN PITCHING MOMENT DUE TO AXIAL FORCE INCREMENT PER SPANWISE FOOT OF CONTROL---------- 0 DELTA = 0.0 2.0 4.0 6.0 10.0 12.0 16.0 20.0 25.0 30.0 ALPHA 0 0.0 0.00E+00 -0.29E-04 0.89E-05 -0.12E-03 -0.97E-03 -0.17E-02 -0.38E-02 -0.65E-02 -0.10E-01 -0.14E-01 5.0 0.00E+00 -0.47E-04 -0.12E-03 -0.30E-03 -0.10E-02 -0.15E-02 -0.30E-02 -0.49E-02 -0.78E-02 -0.11E-01 10.0 0.00E+00 -0.92E-04 -0.28E-03 -0.24E-02 -0.16E-01 -0.32E-01 -0.93E-01 -0.21E+00 -0.49E+00 -0.96E+00 15.0 0.00E+00 -0.14E-03 -0.99E-03 -0.43E-02 -0.26E-01 -0.50E-01 -0.15E+00 -0.34E+00 -0.81E+00 -0.17E+01 20.0 0.00E+00 -0.18E-03 -0.15E-02 -0.57E-02 -0.32E-01 -0.61E-01 -0.17E+00 -0.39E+00 -0.90E+00 -0.18E+01 1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM AERODYNAMIC CONTROL EFFECTIVENESS AT HYPERSONIC SPEEDS FLAT PLATE WITH FLAP IN HYPERSONIC FLOW, EXAMPLE PROBLEM 11 MACH NUMBER=10.00 REYNOLDS NO./FT= 0.11E+06 0 REF. AREA (FT2)= 1.000 MOMENT REFERENCE CENTER = HL LONG. REF. LENGTH(FT)= 1.000 0 ---------- CENTER-OF-PRESSURE LOCATION OF NORMAL FORCE---------- 0 DELTA = 0.0 2.0 4.0 6.0 10.0 12.0 16.0 20.0 25.0 30.0 ALPHA 0 0.0 -0.10E+01 0.36E+01 0.32E+01 0.30E+01 0.30E+01 0.30E+01 0.30E+01 0.31E+01 0.32E+01 5.0 -0.10E+01 0.23E+01 0.26E+01 0.29E+01 0.29E+01 0.30E+01 0.31E+01 0.32E+01 0.33E+01 10.0 -0.10E+01 0.48E-01 -0.58E+00 -0.93E+00 -0.10E+01 -0.11E+01 -0.11E+01 -0.10E+01 -0.10E+01 15.0 -0.10E+01 -0.63E+00 -0.88E+00 -0.10E+01 -0.10E+01 -0.11E+01 -0.11E+01 -0.10E+01 -0.98E+00 20.0 -0.10E+01 -0.82E+00 -0.95E+00 -0.10E+01 -0.10E+01 -0.10E+01 -0.10E+01 -0.10E+01 -0.95E+00 0 ----------CENTER-OF-PRESSURE LOCATION OF AXIAL FORCE---------- 0 DELTA = 0.0 2.0 4.0 6.0 10.0 12.0 16.0 20.0 25.0 30.0 ALPHA 0 0.0 0.35E-01 -0.21E-01 0.80E-01 0.18E+00 0.22E+00 0.29E+00 0.35E+00 0.41E+00 0.45E+00 5.0 0.35E-01 0.92E-01 0.13E+00 0.19E+00 0.22E+00 0.27E+00 0.33E+00 0.38E+00 0.44E+00 10.0 0.35E-01 0.45E-01 0.13E+00 0.23E+00 0.27E+00 0.35E+00 0.43E+00 0.52E+00 0.61E+00 15.0 0.35E-01 0.77E-01 0.13E+00 0.21E+00 0.25E+00 0.33E+00 0.40E+00 0.49E+00 0.58E+00 20.0 0.35E-01 0.79E-01 0.12E+00 0.20E+00 0.24E+00 0.31E+00 0.39E+00 0.47E+00 0.56E+00 1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE. 0 1 END OF JOB.