********************************************************************* * * * PROGRAM TSFOIL * * SOLVES * * INVISCID FLOW PAST THIN TWO DIMENSIONAL LIFTING AIRFOIL * * USING * * TRANSONIC SMALL DISTURBANCE THEORY * * FULLY CONSERVATIVE FINITE DIFFERENCE EQUATIONS * * SUCCESSIVE LINE OVERRELAXATION * * * * WRITTEN BY * * * * EARLL M. MURMAN AND FRANK R. BAILEY * * NASA-AMES RESEARCH CENTER * * MOFFETT FIELD, CALIFORNIA * * AND * * MARGARET L. JOHNSON * * COMPUTER SCIENCES CORPORATION * * MOUNTAIN VIEW, CALIFORNIA * * * ********************************************************************* enter name of input data file SC20610.inp TEST OF DATA POINT INPUT CASE , NASA SC(2)-0610 EMACH = 0.74000 POR = 0.00000 IMIN = 1 BCTYPE = 1 AMESH = T DELTA = 0.10000 CLSET = 0.00000 IMAXI = 81 BCFOIL = 4 PHYS = T ALPHA = 0.00000 EPS = 0.20000 JMIN = 1 PSTART = 1 PSAVE = F AK = 0.00000 RIGF = 0.00000 JMAXI = 64 PRTFLO = 1 KUTTA = T GAM = 1.40000 WCIRC = 1.00000 MAXIT =1000 IPRTER = 10 FCR = T F = 0.00000 CVERGE = 0.00000 NU = 100 SIMDEF = 3 H = 0.00000 DVERGE = 10.0 NL = 75 ICUT = 2 WE = 1.80,1.80,1.70 XIN -4.759090 -1.451373 -1.154130 -0.959227 -0.798421 -0.644242 -0.473078 -0.290925 -0.176356 -0.113082 -0.074485 -0.049489 -0.032465 -0.020228 -0.010907 -0.003416 0.002981 0.008679 0.014039 0.019292 0.024707 0.030523 0.037083 0.044772 0.054190 0.066066 0.081200 0.100083 0.122447 0.147263 0.173324 0.199723 0.225942 0.251747 0.277060 0.301889 0.326276 0.350282 0.373966 0.397389 0.420605 0.443660 0.466597 0.489449 0.512245 0.535006 0.557751 0.580493 0.603241 0.626005 0.648791 0.671609 0.694470 0.717388 0.740383 0.763482 0.786719 0.810138 0.833793 0.857753 0.882101 0.906941 0.932402 0.958646 0.985879 1.014370 1.044481 1.076713 1.111798 1.150867 1.195818 1.250238 1.322245 1.436261 1.647911 1.849817 2.013718 2.177861 2.372788 2.664829 4.821552 YIN -5.200000 -2.594099 -1.722835 -1.285221 -1.021059 -0.843610 -0.715700 -0.618740 -0.542401 -0.480483 -0.429040 -0.385438 -0.347855 -0.314984 -0.285868 -0.259787 -0.236187 -0.214639 -0.194798 -0.176391 -0.159191 -0.143013 -0.127701 -0.113124 -0.099167 -0.085732 -0.072733 -0.060093 -0.047741 -0.035615 -0.023653 -0.011800 0.011800 0.023653 0.035615 0.047741 0.060093 0.072733 0.085732 0.099167 0.113124 0.127701 0.143013 0.159191 0.176391 0.194798 0.214639 0.236187 0.259787 0.285868 0.314984 0.347855 0.385438 0.429040 0.480483 0.542401 0.618740 0.715700 0.843610 1.021059 1.285221 1.722835 2.594099 5.200000 XU 0.000008 0.000167 0.000391 0.000799 0.001407 0.002153 0.003331 0.005336 0.008648 0.014583 0.023481 0.033891 0.040887 0.053973 0.056921 0.058456 0.059966 0.061445 0.062909 0.065925 0.068785 0.071482 0.074007 0.075322 0.076603 0.077862 0.079112 0.080445 0.081819 0.083269 0.084841 0.086702 0.088848 0.091378 0.094413 0.098308 0.103104 0.109010 0.116244 0.125452 0.136635 0.150037 0.165853 0.184699 0.195177 0.206361 0.218244 0.230813 0.244047 0.257917 0.272371 0.287410 0.302990 0.319057 0.335555 0.352421 0.369591 0.386995 0.404133 0.421391 0.438708 0.456013 0.473246 0.490343 0.507242 0.523881 0.539536 0.554867 0.569823 0.584351 0.598405 0.611936 0.624904 0.637273 0.648435 0.659016 0.668987 0.678321 0.687012 0.695090 0.706936 0.728406 0.738649 0.761390 0.777010 0.792241 0.809068 0.824992 0.836953 0.857188 0.875621 0.898268 0.913686 0.927686 0.939804 0.952002 0.971789 0.989100 0.997860 1.000000 YU 0.000787 0.003092 0.004538 0.006137 0.007683 0.009056 0.010675 0.012803 0.015607 0.019624 0.024441 0.029035 0.031698 0.035966 0.036837 0.037277 0.037700 0.038103 0.038497 0.039276 0.039986 0.040625 0.041195 0.041483 0.041756 0.042019 0.042274 0.042539 0.042804 0.043079 0.043368 0.043700 0.044072 0.044497 0.044989 0.045595 0.046312 0.047154 0.048132 0.049301 0.050626 0.052089 0.053663 0.055351 0.056210 0.057068 0.057918 0.058751 0.059559 0.060335 0.061068 0.061751 0.062381 0.062947 0.063445 0.063867 0.064213 0.064473 0.064646 0.064733 0.064735 0.064651 0.064477 0.064218 0.063871 0.063438 0.062945 0.062376 0.061731 0.061014 0.060232 0.059389 0.058496 0.057562 0.056650 0.055721 0.054791 0.053867 0.052965 0.052086 0.050722 0.048045 0.046680 0.043441 0.041053 0.038606 0.035768 0.032958 0.030775 0.026954 0.023361 0.018848 0.015750 0.012954 0.010567 0.008213 0.004559 0.001620 0.000293 0.000000 XL 0.000000 0.000012 0.000043 0.000183 0.000249 0.000348 0.000455 0.000680 0.001011 0.001481 0.001875 0.002316 0.003055 0.004201 0.004747 0.005779 0.007035 0.008265 0.009969 0.012286 0.015346 0.019276 0.025335 0.029379 0.039095 0.052516 0.062469 0.073329 0.085290 0.099822 0.118563 0.140987 0.167184 0.202933 0.228511 0.247895 0.263995 0.282047 0.297045 0.310147 0.324075 0.344872 0.363502 0.387644 0.404492 0.426308 0.450016 0.475378 0.521837 0.549843 0.578612 0.605305 0.623479 0.642152 0.657543 0.671212 0.690340 0.708891 0.726684 0.746683 0.768502 0.784892 0.801149 0.819187 0.838548 0.858817 0.879431 0.903723 0.926504 0.943652 0.958668 0.973623 0.986187 0.996582 1.000000 YL 0.000000 -0.000700 -0.001385 -0.002868 -0.003330 -0.003880 -0.004379 -0.005199 -0.006133 -0.007183 -0.007933 -0.008676 -0.009776 -0.011204 -0.011815 -0.012861 -0.013983 -0.014962 -0.016175 -0.017636 -0.019336 -0.021258 -0.023836 -0.025373 -0.028634 -0.032423 -0.034840 -0.037182 -0.039456 -0.041862 -0.044483 -0.047017 -0.049298 -0.051443 -0.052406 -0.052859 -0.053062 -0.053117 -0.053027 -0.052849 -0.052562 -0.051951 -0.051218 -0.050013 -0.049004 -0.047495 -0.045601 -0.043288 -0.038336 -0.034916 -0.031104 -0.027333 -0.024661 -0.021854 -0.019517 -0.017429 -0.014527 -0.011771 -0.009228 -0.006537 -0.003868 -0.002086 -0.000524 0.000950 0.002227 0.003224 0.003885 0.004212 0.004067 0.003657 0.003067 0.002242 0.001329 0.000376 0.000000 SCALED POR= 0.00000 AIRFOIL GEOMETRY INFORMATION PRINTOUT IN PHYSICAL VARIABLES NORMALIZED BY CHORD LENGTH MAX THICKNESS = 0.099755 AIRFOIL VOLUME = 0.06741506 MAX CAMBER = 0.010200 UPPER SURFACE LOWER SURFACE X Y DY/DX Y DY/DX THICKNESS CAMBER 0.00298125 0.00978288 1.59095562 -0.00978288 -1.59095562 0.00978288 0.00000000 0.00867915 0.01443971 0.82824528 -0.01443971 -0.82824528 0.01443971 0.00000000 0.01403880 0.01805637 0.52051079 -0.01805637 -0.52051073 0.01805637 0.00000000 0.01929164 0.02033265 0.37956822 -0.02033265 -0.37956834 0.02033265 0.00000000 0.02470696 0.02232698 0.35506523 -0.02232698 -0.35506535 0.02232698 0.00000000 0.03052330 0.02426150 0.30597645 -0.02426150 -0.30597574 0.02426150 0.00000000 0.03708321 0.02608277 0.25370559 -0.02608276 -0.25370601 0.02608276 0.00000000 0.04477173 0.02789491 0.22037001 -0.02789493 -0.22037187 0.02789492 -0.00000001 0.05419004 0.02982493 0.19132355 -0.02982489 -0.19131468 0.02982491 0.00000002 0.06606644 0.03195647 0.16813184 -0.03195667 -0.16813463 0.03195657 -0.00000010 0.08119977 0.03427392 0.14473033 -0.03427456 -0.14532100 0.03427424 -0.00000032 0.10008341 0.03670936 0.11218586 -0.03670990 -0.11870735 0.03670963 -0.00000027 0.12244672 0.03915687 0.10338201 -0.03925430 -0.10289942 0.03920558 -0.00004871 0.14726296 0.04145842 0.08957583 -0.04155831 -0.08961871 0.04150837 -0.00004994 0.17332384 0.04343702 0.07166868 -0.04353684 -0.07161330 0.04348693 -0.00004991 0.19972268 0.04508421 0.05711634 -0.04518360 -0.05921808 0.04513391 -0.00004969 0.22594240 0.04640424 0.05046494 -0.04660739 -0.04980826 0.04650582 -0.00010158 0.25174683 0.04747315 0.04195559 -0.04767309 -0.04193289 0.04757312 -0.00009997 0.27706018 0.04830839 0.03068172 -0.04850828 -0.03069445 0.04840833 -0.00009994 0.30188873 0.04893428 0.01833657 -0.04913666 -0.01984361 0.04903547 -0.00010119 0.32627636 0.04943494 0.01970051 -0.04958266 -0.00850002 0.04950880 -0.00007386 0.35028163 0.04970294 0.01041481 -0.04980350 -0.01181797 0.04975322 -0.00005028 0.37396622 0.04994626 0.01142510 -0.04980835 -0.00144589 0.04987730 0.00006895 0.39738923 0.04999676 0.00080589 -0.04962642 0.00976657 0.04981159 0.00018517 0.42060480 0.04999575 -0.00735834 -0.04928815 0.01972353 0.04964195 0.00035380 0.44366038 0.04976214 -0.01041330 -0.04879700 0.03031969 0.04927957 0.00048257 0.46659705 0.04947393 -0.02165518 -0.04803991 0.04165881 0.04875692 0.00071701 0.48944914 0.04901126 -0.02040679 -0.04702768 0.05050635 0.04801947 0.00099179 0.51224482 0.04853985 -0.02837222 -0.04576718 0.05854963 0.04715351 0.00138633 0.53500640 0.04784824 -0.03031126 -0.04425348 0.06902041 0.04605086 0.00179738 0.55775130 0.04709360 -0.04180579 -0.04241024 0.09248167 0.04475192 0.00234168 0.58049279 0.04618096 -0.03853042 -0.04004608 0.10922568 0.04311352 0.00306744 0.60324109 0.04513612 -0.05001568 -0.03741413 0.11849697 0.04127512 0.00386100 0.62600458 0.04400873 -0.04979320 -0.03451503 0.12963265 0.03926188 0.00474685 0.64879102 0.04267678 -0.06254003 -0.03146984 0.14089803 0.03707331 0.00560347 0.67160910 0.04109037 -0.06804316 -0.02815623 0.15119916 0.03462330 0.00646707 0.69446981 0.03933811 -0.08020880 -0.02469297 0.16053666 0.03201554 0.00732257 0.71738797 0.03743718 -0.09141500 -0.02101825 0.16012745 0.02922771 0.00820946 0.74038333 0.03526174 -0.09964136 -0.01733863 0.16011012 0.02630019 0.00896155 0.76348239 0.03282031 -0.10849600 -0.01363709 0.16156851 0.02322870 0.00959161 0.78671944 0.03008964 -0.11936996 -0.01009760 0.15068887 0.02009362 0.00999602 0.81013811 0.02718208 -0.12974034 -0.00678296 0.12334829 0.01698252 0.01019956 0.83379328 0.02397337 -0.13837601 -0.00410860 0.10132195 0.01404099 0.00993238 0.85775286 0.02044311 -0.15110081 -0.00196338 0.07549410 0.01120325 0.00923987 0.88210094 0.01656816 -0.15788577 -0.00061837 0.03633029 0.00859327 0.00797490 0.90694106 0.01242752 -0.17032932 -0.00034748 -0.01397006 0.00638750 0.00604002 0.93240225 0.00785076 -0.18882298 -0.00136654 -0.07339139 0.00460865 0.00324211 0.95864606 0.00277629 -0.20363073 -0.00402805 -0.12612782 0.00340217 -0.00062588 0.98587894 -0.00307957 -0.23863123 -0.00833403 -0.19914131 0.00262723 -0.00570680 WE = 1.8000 EPS = 0.2000 MAXIT FOR THIS MESH = 250 ITER CL CM IERR JERR ERROR IRL JRL BIGRL ERCIRC 10 0.69736 -0.24565 12 8 0.8046E-01 5 8 0.9278E+02 0.6696E-01 20 0.77073 -0.20861 5 2 0.2533E-01 6 2 0.1908E+03 0.1825E-02 30 0.81279 -0.20304 12 8 0.1410E-01 5 8 0.9764E+02 0.9660E-02 40 0.85510 -0.19849 11 8 0.9716E-02 5 8 0.7277E+02 0.6473E-02 50 0.88295 -0.19660 11 8 0.6994E-02 5 8 0.5410E+02 0.4895E-02 60 0.90566 -0.19664 12 8 0.5388E-02 5 8 0.3969E+02 0.4382E-02 70 0.92363 -0.19736 10 9 0.5391E-02 5 8 0.3049E+02 0.4438E-02 80 0.93741 -0.19783 11 9 0.1034E-01 5 8 0.2628E+02 0.7497E-02 90 0.95041 -0.19093 12 9 0.4934E-01 4 9 0.6787E+02 0.3788E-01 100 2.65190 -1.25854 20 15 0.1521E+01 5 13 0.7515E+04 0.5991E+00 110 -0.46903 0.22994 20 8 0.6712E+00 6 4 0.4482E+04 0.2829E+00 120 1.17944 -0.59646 20 15 0.1004E+01 14 8 0.7336E+03 0.9977E-02 130 1.07320 -0.40960 11 8 0.9045E-01 5 8 0.2165E+03 0.4467E-01 140 1.49271 -0.52847 12 8 0.5502E-01 5 8 0.1149E+03 0.9098E-01 150 1.84277 -0.43994 11 9 0.1120E+00 7 9 0.2689E+03 0.1405E+00 160 1.29331 -0.39651 20 8 0.1014E+00 18 9 0.1700E+03 0.2035E+00 170 -0.53644 -0.39722 20 8 0.4389E+01 6 12 0.1359E+05 0.9218E+00 180 0.43838 -1.18736 13 9 0.4714E+01 7 9 0.1009E+05 0.1289E+01 190 1.02790 -0.67099 20 5 0.1528E+01 6 2 0.1565E+04 0.2976E+00 200 -0.57643 0.45102 20 9 0.1432E+01 7 5 0.2722E+04 0.7293E-01 210 3.96089 -0.98534 10 8 0.4894E+01 7 8 0.3679E+05 0.2661E+01 220 1.29294 -1.16179 20 8 0.2493E+01 6 14 0.7110E+04 0.1917E+01 230 -0.42807 0.27558 10 8 0.6624E+00 5 2 0.5305E+04 0.4336E+00 240 0.22112 -0.13512 16 8 0.5953E+00 5 8 0.4670E+03 0.2381E+00 250 0.17083 -0.10310 15 8 0.2853E+00 5 9 0.4263E+03 0.3753E-01 ****** ITERATION LIMIT REACHED ****** FORCE COEFFICIENTS, PRESSURE COEFFICIENT, AND MACH NUMBER (OR SIMILARITY PARAMETER) ON BODY AND DIVIDING STREAM LINE. COARSE MESH CL = 0.170827 CM = -0.103096 CP* = -0.638537 LOWER UPPER Y=0- Y=0+ I X CP M1 CP M1 1 -4.759090 0.024020 0.728410 0.024020 0.728410 B * 2 -0.798421 0.470544 0.462841 0.470544 0.462841 B * 3 -0.176356 0.948369 0.000000 0.948369 0.000000 B * 4 -0.032465 1.139778 0.000000 1.139778 0.000000 B * AIRFOIL LEADING EDGE AIRFOIL LEADING EDGE 5 0.002981 0.175385 0.650646 -0.121526 0.796053 L U * 6 0.024707 -1.410890 1.243868 -1.652266 1.310810 * L U 7 0.054190 -1.459136 1.257534 -1.567652 1.287740 * L U 8 0.122447 -1.491626 1.266653 -1.561792 1.286127 * LU 9 0.225942 -1.524430 1.275794 -1.560882 1.285876 * LU 10 0.326276 -1.549348 1.282694 -1.564974 1.287003 * LU 11 0.420605 -1.579094 1.290883 -1.565523 1.287154 * B 12 0.512245 -1.641184 1.307811 -1.558580 1.285241 * UL 13 0.603241 -1.715322 1.327741 -1.568384 1.287941 * U L 14 0.694470 -1.722283 1.329597 -1.609459 1.299190 * U L 15 0.786719 -1.529131 1.277099 -1.664773 1.314185 * L U 16 0.882101 -0.897149 1.087762 -1.765332 1.341018 * L U 17 0.985879 -0.714342 1.026503 -1.573246 1.289278 * L U AIRFOIL TRAILING EDGE AIRFOIL TRAILING EDGE 18 1.111798 -1.108170 1.154441 -1.108170 1.154441 * B 19 1.322245 -0.862990 1.076580 -0.862990 1.076580 * B 20 2.013718 -0.223383 0.840158 -0.223383 0.840158 B * 21 4.821552 0.688138 0.245067 0.688138 0.245067 B * ***** CAUTION ***** MAXIMUM MACH NUMBER EXCEEDS 1.3 SHOCK JUMPS IN ERROR IF UPSTREAM NORMAL MACH NUMBER GREATER THAN 1.3 Y(J) J= 1 TO 16 -5.200000 -1.021059 -0.542401 -0.347855 -0.236187 -0.159191 -0.099167 -0.047741 0.047741 0.099167 0.159191 0.236187 0.347855 0.542401 1.021059 5.200000 WE = 1.8000 EPS = 0.2000 MAXIT FOR THIS MESH = 500 ITER CL CM IERR JERR ERROR IRL JRL BIGRL ERCIRC 10 0.13276 -0.07737 38 17 0.8132E-01 9 16 0.1056E+04 0.4142E-01 20 0.14127 -0.09534 35 16 0.2650E-01 9 16 0.9273E+03 0.3372E-02 30 0.15696 -0.10973 9 16 0.2197E-01 9 16 0.8339E+03 0.5592E-03 40 0.13760 -0.10081 36 25 0.2871E-01 9 16 0.7614E+03 0.6946E-02 50 0.28318 -0.18728 33 5 0.3324E-01 9 16 0.7056E+03 0.4767E-01 60 0.62857 -0.35045 29 7 0.6246E-01 9 16 0.6266E+03 0.5995E-01 70 0.95217 -0.43154 25 16 0.9106E-01 9 16 0.5365E+03 0.5710E-01 80 1.13140 -0.41507 23 16 0.2381E-01 9 16 0.4387E+03 0.2256E-01 90 1.20157 -0.39277 8 20 0.9027E-02 9 16 0.3239E+03 0.9290E-02 100 1.23363 -0.37107 16 17 0.8102E-02 9 16 0.1732E+03 0.4628E-02 110 1.23140 -0.35049 38 16 0.3341E-01 38 16 0.1818E+03 0.2316E-01 120 1.21767 -0.32939 38 16 0.3750E-01 38 16 0.1931E+03 0.2309E-01 130 1.19254 -0.31038 38 16 0.5094E-01 38 16 0.2629E+03 0.3136E-01 140 1.16542 -0.29330 38 16 0.5941E-01 38 16 0.3105E+03 0.3669E-01 150 1.13654 -0.27753 38 16 0.6276E-01 38 16 0.3312E+03 0.3927E-01 160 1.10963 -0.26469 38 16 0.6287E-01 38 16 0.3345E+03 0.3973E-01 170 1.08371 -0.25322 38 16 0.6053E-01 38 16 0.3236E+03 0.3830E-01 180 1.06017 -0.24398 38 16 0.5633E-01 38 16 0.3018E+03 0.3583E-01 190 1.03827 -0.23580 38 16 0.5224E-01 38 16 0.2809E+03 0.3327E-01 200 1.01813 -0.22886 20 17 0.4831E-01 38 16 0.2576E+03 0.3056E-01 210 0.99999 -0.22302 20 17 0.4578E-01 38 16 0.2356E+03 0.2791E-01 220 0.98329 -0.21796 20 17 0.4317E-01 38 16 0.2134E+03 0.2522E-01 230 0.96833 -0.21385 19 17 0.4077E-01 38 16 0.1918E+03 0.2269E-01 240 0.95468 -0.21028 19 17 0.3840E-01 38 16 0.1736E+03 0.2052E-01 250 0.94231 -0.20728 19 17 0.3617E-01 12 17 0.1665E+03 0.1847E-01 260 0.93131 -0.20486 19 17 0.3408E-01 12 17 0.1631E+03 0.1665E-01 270 0.92130 -0.20275 19 17 0.3208E-01 12 17 0.1599E+03 0.1511E-01 280 0.91222 -0.20097 19 17 0.3022E-01 12 17 0.1566E+03 0.1372E-01 290 0.90408 -0.19954 19 17 0.2851E-01 12 17 0.1527E+03 0.1248E-01 300 0.89668 -0.19829 18 17 0.2695E-01 12 17 0.1491E+03 0.1147E-01 310 0.88992 -0.19721 18 17 0.2556E-01 12 17 0.1458E+03 0.1058E-01 320 0.88379 -0.19630 18 17 0.2429E-01 12 17 0.1428E+03 0.9771E-02 330 0.87827 -0.19555 18 17 0.2313E-01 12 17 0.1400E+03 0.9038E-02 340 0.87324 -0.19492 18 17 0.2211E-01 12 17 0.1377E+03 0.8410E-02 350 0.86863 -0.19437 18 17 0.2124E-01 12 17 0.1359E+03 0.7903E-02 360 0.86441 -0.19389 18 17 0.2043E-01 12 17 0.1341E+03 0.7449E-02 370 0.86057 -0.19348 18 17 0.1968E-01 12 17 0.1325E+03 0.7037E-02 380 0.85706 -0.19313 18 17 0.1899E-01 12 17 0.1310E+03 0.6658E-02 390 0.85386 -0.19282 18 17 0.1836E-01 12 17 0.1296E+03 0.6313E-02 400 0.85095 -0.19256 18 17 0.1778E-01 12 17 0.1283E+03 0.5991E-02 410 0.84827 -0.19233 18 17 0.1724E-01 12 17 0.1271E+03 0.5724E-02 420 0.84581 -0.19212 18 17 0.1674E-01 12 17 0.1260E+03 0.5490E-02 430 0.84356 -0.19194 17 17 0.1632E-01 12 17 0.1250E+03 0.5280E-02 440 0.84149 -0.19177 17 17 0.1594E-01 12 17 0.1240E+03 0.5090E-02 450 0.83959 -0.19162 17 17 0.1560E-01 12 17 0.1231E+03 0.4917E-02 460 0.83784 -0.19149 17 17 0.1527E-01 12 17 0.1222E+03 0.4760E-02 470 0.83623 -0.19137 17 17 0.1498E-01 12 17 0.1215E+03 0.4619E-02 480 0.83476 -0.19126 17 17 0.1471E-01 12 17 0.1208E+03 0.4489E-02 490 0.83340 -0.19116 17 17 0.1445E-01 12 17 0.1201E+03 0.4372E-02 500 0.83215 -0.19107 17 17 0.1422E-01 12 17 0.1195E+03 0.4269E-02 ****** ITERATION LIMIT REACHED ****** FORCE COEFFICIENTS, PRESSURE COEFFICIENT, AND MACH NUMBER (OR SIMILARITY PARAMETER) ON BODY AND DIVIDING STREAM LINE. MEDIUM MESH CL = 0.832145 CM = -0.191070 CP* = -0.638537 LOWER UPPER Y=0- Y=0+ I X CP M1 CP M1 1 -4.759090 -0.009429 0.744500 -0.009429 0.744500 B * 2 -1.154130 0.030876 0.725069 0.030876 0.725069 B * 3 -0.798421 0.064988 0.708206 0.064988 0.708206 B * 4 -0.473078 0.115183 0.682637 0.115183 0.682637 B * 5 -0.176356 0.258011 0.603987 0.258011 0.603987 B * 6 -0.074485 0.489560 0.448050 0.489560 0.448050 B * 7 -0.032465 0.752465 0.120343 0.752465 0.120343 B * 8 -0.010907 0.986647 0.000000 0.986647 0.000000 B * AIRFOIL LEADING EDGE AIRFOIL LEADING EDGE 9 0.002981 1.149820 0.000000 0.525216 0.418912 L U * 10 0.014039 0.185822 0.644939 -0.876769 1.081104 L * U 11 0.024707 -0.034645 0.756403 -1.378357 1.234568 L * U 12 0.037083 -0.112995 0.792248 -1.342572 1.224257 L * U 13 0.054190 -0.122913 0.796670 -1.307973 1.214204 L * U 14 0.081200 -0.125009 0.797602 -1.226686 1.190252 L * U 15 0.122447 -0.135136 0.802087 -1.157375 1.169442 L * U 16 0.173324 -0.144927 0.806399 -1.110704 1.155218 L * U 17 0.225942 -0.157984 0.812115 -1.082901 1.146660 L * U 18 0.277060 -0.174451 0.819267 -1.057366 1.138744 L * U 19 0.326276 -0.172695 0.818507 -1.017873 1.126392 L * U 20 0.373966 -0.178215 0.820893 -0.994263 1.118942 L * U 21 0.420605 -0.193889 0.827629 -0.959103 1.107754 L * U 22 0.466597 -0.184201 0.823472 -0.711350 1.025470 L * U 23 0.512245 -0.172277 0.818326 -0.508219 0.952717 L U * 24 0.557751 -0.136624 0.802744 -0.535181 0.962690 L U * 25 0.603241 -0.057800 0.767171 -0.570846 0.975726 L U* 26 0.648791 0.039484 0.720851 -0.604516 0.987875 L * 27 0.694470 0.165243 0.656145 -0.608470 0.989292 L * 28 0.740383 0.303650 0.576599 -0.570475 0.975591 L U* 29 0.786719 0.450988 0.477574 -0.509303 0.953120 L U * 30 0.833793 0.579629 0.370048 -0.434380 0.924855 L U * 31 0.882101 0.668511 0.271962 -0.359747 0.895812 L U * 32 0.932402 0.666563 0.274488 -0.241427 0.847732 L U * 33 0.985879 0.437628 0.487384 0.023125 0.728846 L U * AIRFOIL TRAILING EDGE AIRFOIL TRAILING EDGE 34 1.044481 0.176911 0.649815 0.176911 0.649815 B * 35 1.111798 0.125064 0.677490 0.125064 0.677490 B * 36 1.195818 0.090603 0.695276 0.090603 0.695276 B * 37 1.322245 0.058766 0.711312 0.058766 0.711312 B * 38 1.647911 0.031567 0.724731 0.031567 0.724731 B * 39 2.013718 0.018053 0.731307 0.018053 0.731307 B * 40 2.372788 0.008817 0.735767 0.008817 0.735767 B * 41 4.821552 -0.002353 0.741126 -0.002353 0.741126 B * Y(J) J= 1 TO 32 -5.200000 -1.722835 -1.021059 -0.715700 -0.542401 -0.429040 -0.347855 -0.285868 -0.236187 -0.194798 -0.159191 -0.127701 -0.099167 -0.072733 -0.047741 -0.023653 0.023653 0.047741 0.072733 0.099167 0.127701 0.159191 0.194798 0.236187 0.285868 0.347855 0.429040 0.542401 0.715700 1.021059 1.722835 5.200000 WE = 1.7000 EPS = 0.2000 MAXIT FOR THIS MESH = 1000 ITER CL CM IERR JERR ERROR IRL JRL BIGRL ERCIRC 10 0.81472 -0.17804 16 33 0.1209E-02 17 32 0.2939E+03 0.1762E-02 20 0.80918 -0.17689 18 33 0.6859E-03 17 32 0.1729E+03 0.7975E-03 30 0.80579 -0.17667 45 32 0.5219E-03 17 32 0.1283E+03 0.5581E-03 40 0.80318 -0.17664 44 32 0.4679E-03 17 32 0.1060E+03 0.4523E-03 50 0.80094 -0.17663 44 32 0.4164E-03 17 32 0.9253E+02 0.3961E-03 60 0.79893 -0.17660 44 32 0.3797E-03 17 32 0.8353E+02 0.3629E-03 70 0.79705 -0.17656 44 32 0.3532E-03 17 32 0.7708E+02 0.3394E-03 80 0.79528 -0.17652 44 32 0.3336E-03 17 32 0.7201E+02 0.3219E-03 90 0.79360 -0.17649 44 32 0.3180E-03 17 32 0.6793E+02 0.3070E-03 100 0.79198 -0.17646 44 32 0.3054E-03 17 32 0.6449E+02 0.2941E-03 110 0.79044 -0.17643 44 32 0.2941E-03 17 32 0.6157E+02 0.2818E-03 120 0.78896 -0.17641 44 32 0.2842E-03 17 32 0.5899E+02 0.2704E-03 130 0.78754 -0.17639 44 32 0.2750E-03 17 32 0.5665E+02 0.2595E-03 140 0.78617 -0.17638 44 32 0.2666E-03 17 32 0.5465E+02 0.2491E-03 150 0.78486 -0.17637 44 32 0.2587E-03 17 32 0.5283E+02 0.2389E-03 160 0.78361 -0.17636 44 32 0.2511E-03 17 32 0.5116E+02 0.2290E-03 170 0.78240 -0.17636 44 32 0.2438E-03 17 32 0.4957E+02 0.2201E-03 180 0.78124 -0.17636 44 32 0.2369E-03 17 32 0.4816E+02 0.2111E-03 190 0.78013 -0.17636 44 32 0.2303E-03 17 32 0.4679E+02 0.2028E-03 200 0.77906 -0.17636 44 32 0.2241E-03 17 32 0.4553E+02 0.1951E-03 210 0.77804 -0.17636 44 32 0.2180E-03 17 32 0.4434E+02 0.1879E-03 220 0.77705 -0.17637 44 32 0.2122E-03 17 32 0.4317E+02 0.1805E-03 230 0.77610 -0.17637 44 32 0.2066E-03 17 32 0.4206E+02 0.1737E-03 240 0.77518 -0.17638 44 32 0.2013E-03 17 32 0.4104E+02 0.1673E-03 250 0.77430 -0.17638 44 32 0.1961E-03 17 32 0.4005E+02 0.1614E-03 260 0.77345 -0.17639 44 32 0.1911E-03 17 32 0.3909E+02 0.1557E-03 270 0.77262 -0.17640 44 32 0.1863E-03 17 32 0.3822E+02 0.1502E-03 280 0.77183 -0.17640 44 32 0.1818E-03 17 32 0.3728E+02 0.1452E-03 290 0.77106 -0.17641 44 32 0.1774E-03 17 32 0.3638E+02 0.1404E-03 300 0.77032 -0.17642 44 32 0.1731E-03 17 32 0.3560E+02 0.1357E-03 310 0.76960 -0.17643 44 32 0.1689E-03 17 32 0.3482E+02 0.1322E-03 320 0.76890 -0.17644 44 32 0.1649E-03 17 32 0.3407E+02 0.1277E-03 330 0.76823 -0.17645 44 32 0.1612E-03 17 32 0.3332E+02 0.1240E-03 340 0.76757 -0.17646 44 32 0.1574E-03 17 32 0.3261E+02 0.1200E-03 350 0.76694 -0.17646 44 32 0.1539E-03 17 32 0.3189E+02 0.1165E-03 360 0.76632 -0.17647 44 32 0.1503E-03 17 32 0.3120E+02 0.1129E-03 370 0.76572 -0.17648 44 32 0.1471E-03 17 32 0.3061E+02 0.1098E-03 380 0.76514 -0.17649 44 32 0.1439E-03 17 32 0.2992E+02 0.1068E-03 390 0.76457 -0.17649 44 32 0.1408E-03 17 32 0.2933E+02 0.1038E-03 400 0.76402 -0.17650 44 32 0.1377E-03 17 32 0.2869E+02 0.1006E-03 410 0.76349 -0.17650 44 32 0.1348E-03 17 32 0.2815E+02 0.9823E-04 420 0.76297 -0.17651 44 32 0.1319E-03 17 32 0.2756E+02 0.9525E-04 430 0.76246 -0.17651 44 32 0.1292E-03 17 32 0.2698E+02 0.9298E-04 440 0.76197 -0.17652 44 32 0.1266E-03 17 32 0.2648E+02 0.9024E-04 450 0.76149 -0.17653 44 32 0.1239E-03 17 32 0.2598E+02 0.8833E-04 460 0.76102 -0.17653 44 32 0.1215E-03 17 32 0.2543E+02 0.8595E-04 470 0.76056 -0.17654 44 32 0.1190E-03 17 32 0.2493E+02 0.8404E-04 480 0.76012 -0.17654 44 32 0.1166E-03 17 32 0.2449E+02 0.8178E-04 490 0.75968 -0.17655 44 32 0.1141E-03 17 32 0.2399E+02 0.7999E-04 500 0.75925 -0.17656 44 32 0.1121E-03 17 32 0.2352E+02 0.7820E-04 510 0.75884 -0.17656 44 32 0.1099E-03 17 32 0.2305E+02 0.7594E-04 520 0.75843 -0.17657 44 32 0.1078E-03 17 32 0.2266E+02 0.7415E-04 530 0.75804 -0.17657 44 32 0.1057E-03 17 32 0.2220E+02 0.7260E-04 540 0.75765 -0.17658 44 32 0.1037E-03 17 32 0.2183E+02 0.7129E-04 550 0.75727 -0.17658 44 32 0.1017E-03 17 32 0.2140E+02 0.6950E-04 560 0.75690 -0.17659 44 32 0.9989E-04 17 32 0.2097E+02 0.6795E-04 570 0.75654 -0.17659 44 32 0.9794E-04 17 32 0.2066E+02 0.6652E-04 580 0.75619 -0.17660 44 32 0.9601E-04 17 32 0.2027E+02 0.6497E-04 590 0.75584 -0.17660 44 32 0.9425E-04 17 32 0.1990E+02 0.6354E-04 600 0.75550 -0.17660 44 32 0.9259E-04 17 32 0.1954E+02 0.6211E-04 610 0.75517 -0.17661 44 32 0.9087E-04 17 32 0.1920E+02 0.6104E-04 620 0.75485 -0.17661 44 32 0.8931E-04 17 32 0.1881E+02 0.5972E-04 630 0.75453 -0.17661 44 32 0.8774E-04 17 32 0.1848E+02 0.5805E-04 640 0.75422 -0.17661 44 32 0.8621E-04 17 32 0.1814E+02 0.5710E-04 650 0.75392 -0.17662 44 32 0.8462E-04 17 32 0.1790E+02 0.5591E-04 660 0.75362 -0.17662 44 32 0.8313E-04 17 32 0.1751E+02 0.5448E-04 670 0.75333 -0.17662 44 32 0.8159E-04 17 32 0.1726E+02 0.5305E-04 680 0.75305 -0.17662 44 32 0.8017E-04 17 32 0.1694E+02 0.5257E-04 690 0.75277 -0.17662 44 32 0.7884E-04 17 32 0.1665E+02 0.5126E-04 700 0.75249 -0.17663 44 32 0.7743E-04 17 32 0.1637E+02 0.5019E-04 710 0.75222 -0.17663 44 32 0.7614E-04 17 32 0.1611E+02 0.4947E-04 720 0.75196 -0.17663 44 32 0.7480E-04 17 32 0.1581E+02 0.4852E-04 730 0.75170 -0.17663 44 32 0.7349E-04 17 32 0.1554E+02 0.4733E-04 740 0.75145 -0.17663 44 32 0.7225E-04 17 32 0.1531E+02 0.4637E-04 750 0.75120 -0.17663 44 32 0.7106E-04 17 32 0.1506E+02 0.4554E-04 760 0.75096 -0.17663 44 32 0.6986E-04 17 32 0.1478E+02 0.4482E-04 770 0.75072 -0.17664 44 32 0.6871E-04 17 32 0.1451E+02 0.4387E-04 780 0.75049 -0.17664 44 32 0.6755E-04 17 32 0.1430E+02 0.4327E-04 790 0.75026 -0.17664 44 32 0.6649E-04 17 32 0.1404E+02 0.4232E-04 800 0.75003 -0.17664 44 32 0.6534E-04 17 32 0.1383E+02 0.4148E-04 810 0.74981 -0.17664 44 32 0.6429E-04 17 32 0.1363E+02 0.4077E-04 820 0.74959 -0.17664 44 32 0.6319E-04 17 32 0.1339E+02 0.3982E-04 830 0.74938 -0.17664 44 32 0.6210E-04 17 32 0.1321E+02 0.3934E-04 840 0.74917 -0.17664 44 32 0.6111E-04 17 32 0.1295E+02 0.3862E-04 850 0.74897 -0.17664 44 32 0.6032E-04 17 32 0.1275E+02 0.3803E-04 860 0.74876 -0.17664 44 32 0.5925E-04 17 32 0.1258E+02 0.3743E-04 870 0.74857 -0.17665 44 32 0.5830E-04 17 32 0.1237E+02 0.3684E-04 880 0.74837 -0.17665 44 32 0.5739E-04 17 32 0.1218E+02 0.3564E-04 890 0.74818 -0.17665 44 32 0.5647E-04 17 32 0.1200E+02 0.3505E-04 900 0.74799 -0.17665 44 32 0.5555E-04 17 32 0.1177E+02 0.3457E-04 910 0.74781 -0.17665 44 32 0.5468E-04 17 32 0.1163E+02 0.3421E-04 920 0.74763 -0.17665 44 32 0.5383E-04 17 32 0.1140E+02 0.3338E-04 930 0.74745 -0.17665 44 32 0.5297E-04 17 32 0.1124E+02 0.3278E-04 940 0.74727 -0.17665 44 32 0.5211E-04 17 32 0.1107E+02 0.3219E-04 950 0.74710 -0.17665 44 32 0.5120E-04 17 32 0.1090E+02 0.3207E-04 960 0.74693 -0.17665 44 32 0.5061E-04 17 32 0.1075E+02 0.3111E-04 970 0.74677 -0.17666 44 32 0.4973E-04 17 32 0.1056E+02 0.3099E-04 980 0.74660 -0.17666 44 32 0.4902E-04 17 32 0.1036E+02 0.3028E-04 990 0.74644 -0.17666 44 32 0.4837E-04 17 32 0.1025E+02 0.2968E-04 1000 0.74628 -0.17666 44 32 0.4753E-04 17 32 0.1011E+02 0.2921E-04 ****** ITERATION LIMIT REACHED ****** PRINTOUT IN PHYSICAL VARIABLES. DEFINITION OF SIMILARITY PARAMETERS BY KRUPP BOUNDARY CONDITION FOR FREE AIR DIFFERENCE EQUATIONS ARE FULLY CONSERVATIVE. KUTTA CONDITION IS ENFORCED. MACH = 0.7400000 DELTA = 0.1000000 ALPHA = 0.0000000 K = 2.8376412 DOUBLET STRENGTH = 0.6741506 PARAMETERS USED TO TRANSFORM VARIABLES TO TRANSONIC SCALING CPFACT = 0.2700285 CDFACT = 0.0270028 CMFACT = 0.2700285 CLFACT = 0.2700285 YFACT = 2.5044794 VFACT = 5.7295780 FORCE COEFFICIENTS, PRESSURE COEFFICIENT, AND MACH NUMBER (OR SIMILARITY PARAMETER) ON BODY AND DIVIDING STREAM LINE. FINAL MESH CL = 0.746282 CM = -0.176658 CP* = -0.638537 LOWER UPPER Y=0- Y=0+ I X CP M1 CP M1 1 -4.759090 -0.002756 0.741318 -0.002756 0.741318 B * 2 -1.451373 0.016088 0.732258 0.016088 0.732258 B * 3 -1.154130 0.028538 0.726210 0.028538 0.726210 B * 4 -0.959227 0.035160 0.722973 0.035160 0.722973 B * 5 -0.798421 0.043668 0.718792 0.043668 0.718792 B * 6 -0.644242 0.056703 0.712339 0.056703 0.712339 B * 7 -0.473078 0.081177 0.700062 0.081177 0.700062 B * 8 -0.290925 0.129767 0.675026 0.129767 0.675026 B * 9 -0.176356 0.206492 0.633483 0.206492 0.633483 B * 10 -0.113082 0.302246 0.577460 0.302246 0.577460 B * 11 -0.074485 0.411772 0.505828 0.411772 0.505828 B * 12 -0.049489 0.534897 0.410643 0.534897 0.410643 B * 13 -0.032465 0.670913 0.268815 0.670913 0.268815 B * 14 -0.020228 0.819730 0.000000 0.819730 0.000000 B * 15 -0.010907 0.982652 0.000000 0.982652 0.000000 B * 16 -0.003416 1.163348 0.000000 1.163348 0.000000 B * AIRFOIL LEADING EDGE AIRFOIL LEADING EDGE 17 0.002981 1.606684 0.000000 0.742099 0.147737 L U * 18 0.008679 0.692169 0.239168 -0.407263 0.914409 L U * 19 0.014039 0.313912 0.570259 -1.119868 1.158024 L * U 20 0.019292 0.183665 0.646123 -1.345094 1.224987 L * U 21 0.024707 0.115796 0.682319 -1.214035 1.186481 L * U 22 0.030523 0.043051 0.719096 -1.181128 1.176615 L * U 23 0.037083 0.002186 0.738953 -1.178868 1.175935 L * U 24 0.044772 -0.014318 0.746823 -1.172370 1.173975 L * U 25 0.054190 -0.025761 0.752231 -1.153487 1.168264 L * U 26 0.066066 -0.039785 0.758807 -1.125720 1.159813 L * U 27 0.081200 -0.061885 0.769055 -1.117555 1.157317 L * U 28 0.100083 -0.075469 0.775287 -1.093949 1.150068 L * U 29 0.122447 -0.084112 0.779226 -1.044219 1.134647 L * U 30 0.147263 -0.106655 0.789408 -1.018966 1.126735 L * U 31 0.173324 -0.125052 0.797621 -1.008473 1.123431 L * U 32 0.199723 -0.132040 0.800718 -0.983988 1.115684 L * U 33 0.225942 -0.140454 0.804432 -0.951583 1.105347 L * U 34 0.251747 -0.155057 0.810837 -0.932993 1.099373 L * U 35 0.277060 -0.168850 0.816841 -0.925244 1.096873 L * U 36 0.301889 -0.173567 0.818884 -0.848983 1.071961 L * U 37 0.326276 -0.161940 0.813839 -0.631777 0.997602 L U* 38 0.350282 -0.166750 0.815930 -0.502199 0.950477 L U * 39 0.373966 -0.190627 0.826231 -0.567998 0.974692 L U * 40 0.397389 -0.198878 0.829762 -0.635358 0.998873 L U* 41 0.420605 -0.200719 0.830547 -0.633692 0.998282 L U* 42 0.443660 -0.199771 0.830143 -0.657262 1.006611 L * 43 0.466597 -0.191875 0.826766 -0.638539 1.000001 L * 44 0.489449 -0.180847 0.822028 -0.608151 0.989177 L U* 45 0.512245 -0.176240 0.820040 -0.618394 0.992839 L U* 46 0.535006 -0.181979 0.822515 -0.629761 0.996886 L U* 47 0.557751 -0.166825 0.815962 -0.609464 0.989648 L U* 48 0.580493 -0.118551 0.794728 -0.601220 0.986692 L U* 49 0.603241 -0.070543 0.773032 -0.609985 0.989834 L U* 50 0.626005 -0.027054 0.752840 -0.622678 0.994366 L U* 51 0.648791 0.022613 0.729094 -0.640661 1.000752 L * 52 0.671609 0.080021 0.700646 -0.629616 0.996835 L U* 53 0.694470 0.148936 0.664891 -0.629168 0.996676 L U* 54 0.717388 0.218747 0.626593 -0.587568 0.981778 L U* 55 0.740383 0.282779 0.589282 -0.549544 0.967961 L U * 56 0.763482 0.358407 0.541914 -0.523076 0.958226 L U * 57 0.786719 0.443952 0.482765 -0.491219 0.946375 L U * 58 0.810138 0.510864 0.430877 -0.449479 0.930620 L U * 59 0.833793 0.560605 0.387832 -0.410373 0.915613 L U * 60 0.857753 0.612818 0.336781 -0.363337 0.897231 L U * 61 0.882101 0.657856 0.285503 -0.314782 0.877851 L U * 62 0.906941 0.678388 0.258777 -0.271789 0.860326 L U * 63 0.932402 0.657342 0.286141 -0.201804 0.831010 L U * 64 0.958646 0.592711 0.357306 -0.103360 0.787928 L U * 65 0.985879 0.402543 0.512250 0.104255 0.688285 L U * AIRFOIL TRAILING EDGE AIRFOIL TRAILING EDGE 66 1.014370 0.213875 0.629341 0.213875 0.629341 B * 67 1.044481 0.171047 0.653004 0.171047 0.653004 B * 68 1.076713 0.142864 0.668118 0.142864 0.668118 B * 69 1.111798 0.121427 0.679389 0.121427 0.679389 B * 70 1.150867 0.103840 0.688499 0.103840 0.688499 B * 71 1.195818 0.088592 0.696299 0.088592 0.696299 B * 72 1.250238 0.074607 0.703378 0.074607 0.703378 B * 73 1.322245 0.060654 0.710371 0.060654 0.710371 B * 74 1.436261 0.045474 0.717901 0.045474 0.717901 B * 75 1.647911 0.031960 0.724539 0.031960 0.724539 B * 76 1.849817 0.023509 0.728659 0.023509 0.728659 B * 77 2.013718 0.018688 0.730999 0.018688 0.730999 B * 78 2.177861 0.015386 0.732598 0.015386 0.732598 B * 79 2.372788 0.012611 0.733938 0.012611 0.733938 B * 80 2.664829 0.007681 0.736314 0.007681 0.736314 B * 81 4.821552 0.000479 0.739771 0.000479 0.739771 B * Y(J) J= 1 TO 64 -5.200000 -2.594099 -1.722835 -1.285221 -1.021059 -0.843610 -0.715700 -0.618740 -0.542401 -0.480483 -0.429040 -0.385438 -0.347855 -0.314984 -0.285868 -0.259787 -0.236187 -0.214639 -0.194798 -0.176391 -0.159191 -0.143013 -0.127701 -0.113124 -0.099167 -0.085732 -0.072733 -0.060093 -0.047741 -0.035615 -0.023653 -0.011800 0.011800 0.023653 0.035615 0.047741 0.060093 0.072733 0.085732 0.099167 0.113124 0.127701 0.143013 0.159191 0.176391 0.194798 0.214639 0.236187 0.259787 0.285868 0.314984 0.347855 0.385438 0.429040 0.480483 0.542401 0.618740 0.715700 0.843610 1.021059 1.285221 1.722835 2.594099 5.200000 FLOW AT EACH GRID POINT. P PARABOLIC H HYPERBOLIC S SHOCK - ELLIPTIC 64 ------------------------------------------------------------------------------- 63 ------------------------------------------------------------------------------- 62 ------------------------------------------------------------------------------- 61 ------------------------------------------------------------------------------- 60 ------------------------------------------------------------------------------- 59 ------------------------------------------------------------------------------- 58 ------------------------------------------------------------------------------- 57 ------------------------------------------------------------------------------- 56 ------------------------------------------------------------------------------- 55 ------------------------------------------------------------------------------- 54 ------------------------------------------------------------------------------- 53 ------------------------------------------------------------------------------- 52 ------------------------------------------------------------------------------- 51 -------------------------------PHS--------------------------------------------- 50 ------------------------------PHHHS-------------------------------------------- 49 -----------------------------PHHHHS-------------------------------------------- 48 ----------------------------PHHHHHS-------------------------------------------- 47 ----------------------------PHHHHHS-------------------------------------------- 46 ---------------------------PHHHHHHHS------------------------------------------- 45 ---------------------------PHHHHHHHS------------------------------------------- 44 --------------------------PHHHHHHHHS------------------------------------------- 43 --------------------------PHHHHHHHHS------------------------------------------- 42 -------------------------PHHHHHHHHHS------------------------------------------- 41 -------------------------PHHHHHHHHHS------------------------------------------- 40 ------------------------PHHHHHHHHHHS------------------------------------------- 39 ------------------------PHHHHHHHHHHS------------------------------------------- 38 -----------------------PHHHHHHHHHHHS------------------------------------------- 37 ----------------------PHHHHHHHHHHHHS------------------------------------------- 36 ----------------------PHHHHHHHHHHHHS------------------------------------------- 35 --------------------PHHHHHHHHHHHHHHS------------------------------------------- 34 -------------------PHHHHHHHHHHHHHHHS----PS------------------------------------- 33 -----------------PHHHHHHHHHHHHHHHHHS----PS------------------------------------- 32 ------------------------------------------------------------------------------- 31 ------------------------------------------------------------------------------- 30 ------------------------------------------------------------------------------- 29 ------------------------------------------------------------------------------- 28 ------------------------------------------------------------------------------- 27 ------------------------------------------------------------------------------- 26 ------------------------------------------------------------------------------- 25 ------------------------------------------------------------------------------- 24 ------------------------------------------------------------------------------- 23 ------------------------------------------------------------------------------- 22 ------------------------------------------------------------------------------- 21 ------------------------------------------------------------------------------- 20 ------------------------------------------------------------------------------- 19 ------------------------------------------------------------------------------- 18 ------------------------------------------------------------------------------- 17 ------------------------------------------------------------------------------- 16 ------------------------------------------------------------------------------- 15 ------------------------------------------------------------------------------- 14 ------------------------------------------------------------------------------- 13 ------------------------------------------------------------------------------- 12 ------------------------------------------------------------------------------- 11 ------------------------------------------------------------------------------- 10 ------------------------------------------------------------------------------- 9 ------------------------------------------------------------------------------- 8 ------------------------------------------------------------------------------- 7 ------------------------------------------------------------------------------- 6 ------------------------------------------------------------------------------- 5 ------------------------------------------------------------------------------- 4 ------------------------------------------------------------------------------- 3 ------------------------------------------------------------------------------- 2 ------------------------------------------------------------------------------- 1 ------------------------------------------------------------------------------- MACH NO. MAP. ROUNDED TO NEAREST .1 88888888888888888888888888888888888888888888888888888888888888888888888888888887 88888888888888888888888888888888888888888888888888888888888888888888888888888887 78888888888888888888888888888888888888888888888888888888888888888888888888888877 78888888888888888888888888888888888888888888888888888888888888888888888888888777 77788888888888888888888888888888888999999988888888888888888888888888888888887777 77778888888888888888888888889999999999999999999999888888888888888888888888777777 77777888888888888888888888999999999999999999999999999888888888888888888888777777 77777788888888888888888899999999999999999999999999999998888888888888888887777777 77777788888888888888888999999999999999999999999999999999888888888888888877777777 77777788888888888888888999999999999999999999999999999999888888888888888877777777 777777788888888888888899999999****9999999999999999999999988888888888888777777777 77777778888888888888889999999******999999999999999999999988888888888887777777777 7777777788888888888889999999********99999999999999999999998888888888887777777777 7777777788888888888889999999*********9999999999999999999998888888888877777777777 777777777888888888888999999**************999999999999999998888888888777777777777 777777777888888888888999999*****************999999999999998888888887777777777777 77777777778888888888899999*******************99999999999998888888887777777777777 77777777778888888888899999*********************999999999999888888877777777777777 77777777777888888888899999*****1*****************9999999999888888877777777777777 7777777777788888888889999****1111*****************999999999888888777777777777777 7777777777778888888899999***11111******************99999999888888777777777777777 7777777777777888888899999***111111*****************99999999888887777777777777777 777777777777788888889999***1111111******************9999999888887777777777777777 777777777777778888889999***1111111******************9999999888887777777777777777 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77777777777777777777777777777777777777777777777777777777777777777777777777777777 77777777777777777777777777777777777777777777777777777777777777777777777777777777 77777777777777777777777777777777777777777777777777777777777777777777777777777777 L T PRINTER PLOT OF CP ON BODY AND DIVIDING STREAMLINE U FOR CP(UPPER) L FOR CP(LOWER) B FOR CP(UPPER)=CP(LOWER) --- FOR CP SONIC U U U U UU U UUU UUU U U - - - - - - - - ------------U-UUUUUUUUUU------------- -- - - - - - - - - U U U UU U U U U U LLLLLLLLL U LLLL L LL L U LL L B B B B L L B B B B B B B B B L U B BB B B L L BB B L BB L B L L L B L L B L L L L BL LL U B B B L SONIC LINE COORDINATES Y XSONIC 0.31498 0.20866 0.26060 0.28587 0.17737 0.28094 0.25979 0.15774 0.28974 0.23619 0.14131 0.29626 0.21464 0.12776 0.30162 0.19480 0.11619 0.30589 0.17639 0.10591 0.30924 0.15919 0.09635 0.31196 0.14301 0.08821 0.31422 0.12770 0.07973 0.31611 0.11312 0.07276 0.31773 0.09917 0.06511 0.31913 0.08573 0.05849 0.32034 0.07273 0.05145 0.32139 0.06009 0.04437 0.32231 0.04774 0.03749 0.32312 0.03561 0.03025 0.32382 0.02365 0.02187 0.32444 0.44006 0.44857 0.01180 0.01324 0.32499 0.43213 0.45868 BODY LOCATION SONIC LINE PLOT Y VS X * FOR SONIC POINTS + + + + + + + + + + + ....................................................................................................... 1.5 + . . + . . . . . . . . . . . . . . . . . . 1.0 + . . + . . . . . . . . . . . . . . . . . . 0.5 + . . + . . . . . . . ** ** . . * * . . ** * . . ** ** . . ** * . . ** * . 0.0 + . *-----------*--B**Y SLIT--------------- . + . . . . . . . . . . . . . . . . . . -0.5 + . . + . . . . . . . . . . . . . . . . . . -1.0 + . . + ....................................................................................................... + + + + + + + + + + + -0.75 -0.50 -0.25 0.00 0.25 0.50 0.75 1.00 1.25 1.50 1.75 ( 42 PTS) INVISCID WAKE PROFILES FOR INDIVIDUAL SHOCK WAVES WITHIN MOMENTUM CONTOUR SHOCK 1 WAVE DRAG FOR THIS SHOCK= 0.000234 Y CD(Y) PO/POINF 0.00000000 0.00207297 0.99865413 0.01179969 0.00194164 0.99873942 0.02365306 0.00181541 0.99882138 0.03561476 0.00168376 0.99890685 0.04774144 0.00154954 0.99899399 0.06009285 0.00141471 0.99908149 0.07273307 0.00128058 0.99916857 0.08573191 0.00114815 0.99925458 0.09916655 0.00101821 0.99933892 0.11312358 0.00089152 0.99942118 0.12770136 0.00076887 0.99950081 0.14301318 0.00065116 0.99957722 0.15919104 0.00053945 0.99964976 0.17639069 0.00043500 0.99971759 0.19479820 0.00033926 0.99977976 0.21463855 0.00026287 0.99982935 0.23618728 0.00020454 0.99986720 0.25978664 0.00014771 0.99990410 0.28586808 0.00009727 0.99993688 0.31498396 0.00001763 0.99998856 SHOCK 2 WAVE DRAG FOR THIS SHOCK= 0.000000 Y CD(Y) PO/POINF 0.00000000 0.00000046 0.99999970 0.01179969 0.00000034 0.99999976 0.02365306 0.00000025 0.99999982 CALCULATION OF DRAG COEFFICIENT BY MOMENTUM INTEGRAL METHOD BOUNDARIES OF CONTOUR USED CONTRIBUTION TO CD UPSTREAM X = -0.176356 CDUP = -0.002188 DOWNSTREAM X = 1.322245 CDDOWN = 0.002134 TOP Y = 2.594099 CDTOP = 0.000079 BOTTOM Y = -2.594099 CDBOT = 0.000101 TOTAL CONTRIBUTIONS AROUND CONTOUR = 0.000126 THERE ARE 2 SHOCKS INSIDE CONTOUR. TOTAL CDWAVE = 0.000234 NOTE - ALL SHOCKS CONTAINED WITHIN CONTOUR CDWAVE EQUALS TOTAL WAVE DRAG DRAG CALCULATED FROM MOMENTUM INTEGRAL CD = 0.000360 STOP