1.   Total lift coeff.           (W-bar)         +2.000E-01
2.   Zero-lift Moment Coeff.     (C-m,0)         -1.000E-01
3.   C.G. distance from wing AC  (l^-cg)         -5.600E-02
4.   Area of Wing, ft^2          (S-1)           +4.000E+02
5.   Area of H. tail, ft^2       (S-2)           +8.810E+01
6.   Span of Wing, ft            (b-1)           +3.750E+01
7.   Span of H. tail, ft         (b-2)           +1.470E+01
8.   Wing AC to H. tail AC, ft   (l-2)           +1.493E+01
9.   Wing AC to jet nozzle, ft   (l-3)           +1.920E+01
10.  Influence coeff-wing        (sigma/e-11)    +1.000E+00
11.  Influence coeff-H tail      (sigma/e-22)    +1.000E+00
12.  Influence coeff-wing-tail   (sigma/e-12)    +1.160E-01
13.  Induced lift parameter W-THR(k1)            +0.000E+00
14.  Induced lift parameter T-THR(k2)            +0.000E+00
15.  Fraction of thrust-loss     (MU-TL)         +5.000E-01
16.  Thrust coefficient          (C-T)           +2.000E-01
17.  Free stream Mach number     (M-infinity)    +5.000E-01
18.  Wing max thickness swp, rad (lambda-t/c-1)  +3.491E-01
19.  Tail max thickness swp, rad (lambda-t/c-2)  +6.981E-01
20.  Wing incident angle, rad    (i-1)           +0.000E-00
21.  Exhaust Nozzle height, ft   (z-3)           +0.000E+00
22.  Wing chord/4 sweep, rad     (lambda-c/4-1)  +3.491E-01
23.  H tail chord/4 swp, rad     (lambda-c/4-2)  +6.981E-01
24.  Flap chord/total wing chord (c-f/c-w)       +2.000E-01
25.  Wing thickness ratio        (t/c-1)         +8.000E-02
26.  Optimal flap deflection,rad (delta-f)       +0.000E-00
28.  Taper ratio of wing         (TR-1)          +3.500E-01
29.  Taper ratio of H tail       (TR-2)          +4.600E-01
30.  H. Tail Height, ft          (h-2)           +5.335E-01
35.  Elevator-tail chord ratio   (c-e/c-t)       +0.000E-00
36.  H tail tickness ratio       (t/c-2)         +6.200E-02
37.  H tail incident angle, rad  (i-tail)        +9.999E-00