1.   Total lift coeff.           (W-bar)         +1.600E-00
2.   Zero-lift Moment Coeff.     (C-m,0)         -1.000E-01
3.   C.G. distance from wing AC  (l^-cg)         -1.500E-01
4.   Area of Wing, ft^2          (S-1)           +1.670E+02
5.   Area of H. tail, ft^2       (S-2)           +4.140E+01
6.   Area of Canard, ft^2        (S-3)           +2.230E+01
7.   Span of Wing, ft            (b-1)           +4.650E+01
8.   Span of H. tail, ft         (b-2)           +1.370E+01
9.   Span of Canard, ft          (b-3)           +1.060E+01
10.  Wing AC to H. tail AC, ft   (l-2)           +1.551E+01
11.  Wing AC to Canard AC, ft    (l-3)           -2.155E+01
12.  Influence coeff-wing        (sigma/e-11)    +1.000E+00
13.  Influence coeff-H tail      (sigma/e-22)    +1.000E+00
14.  Influence coeff-canard      (sigma/e-33)    +1.000E+00
15.  Influence coeff-wing-tail   (sigma/e-12)    +2.030E-01
16.  Influence coeff-wing-canard (sigma/e-13)    +1.900E-01
17.  Influence coeff-tail-canard (sigma/e-23)    +1.440E-01
18.  Wing Mean chord length, ft  (c-bar)         +3.591E+00
19.  Free stream Mach number     (M-infinity)    +5.000E-01
20.  Wing max thickness swp, rad (lambda-t/c-1)  +0.000E+00
21.  Tail max thickness swp, rad (lambda-t/c-2)  +4.363E-01
22.  Canard max thick. swp, rad  (lambda-t/c-3)  +0.000E+00
23.  Wing chord/4 sweep, rad     (lambda-c/4-1)  +0.000E+00
24.  H tail chord/4 swp, rad     (lambda-c/4-2)  +4.363E-01
25.  Canard chord/4 swp, rad     (lambda-c/4-3)  +0.000E+00
26.  Flap chord/total wing chord (c-f/c-w)       +2.000E-01
27.  Wing thickness ratio        (t/c-1)         +1.000E-01
28.  Optimal flap deflection,rad (delta-f)       +1.745E-02
29.  Incident angle of wing,rad  (i-wing)        +3.491E-02
30.  Taper ratio of wing         (TR-1)          +7.500E-01
31.  Taper ratio of H tail       (TR-2)          +8.200E-01
32.  Taper ratio of canard       (TR-3)          +9.000E-01
33.  H. Tail Height, ft          (h-2)           +6.464E+00
34.  Canard height, ft           (h-3)           -2.227E+00
35.  Elevator-tail chord ratio   (c-e/c-t)       +0.000E-00
36.  H tail tickness ratio       (t/c-2)         +1.200E-01
37.  H tail incident angle, rad  (i-tail)        +0.000E-00
38.  Canard flap-chord ratio     (c-cf/c-c)      +0.000E-00
39.  Canard thickness ratio      (t/c-3)         +8.000E-02
40.  Canard incident angle, rad  (i-canard)      +0.000E-00