dc9 jan 26 example Mar 97 run
0.002376900      < Atmospheric density (slug/ft^3) 
95000.0          < Weight of aircraft (lbs) 
1000.0           < Wing area (ft^2) 
2.000            < CLmax - maximum lift coefficient of the aircraft 
0.30             < CLgrd - lift coefficient for ground run 
1.6500           < CLair - lift coefficient for climb segment 
.080             < CDgrd - drag coefficient for ground run 
0.121            < CDair - drag coefficient for climb segment 
.025             < MUgrd - rolling friction coefficient 
.3               < MUbrk - braking friction coefficient 
0.0              < lambda - thrust deflection angle 
1.1              < k - stall margin 
3.0              < Time between engine failure and braking (sec) 
35.              < Obstacle height (ft) 
2                < Number of engines 
31450.0  29835.0  28475.0 < 3 thrusts (lbs) 
0.  111.6  334.0          < 3 velocities (for thrusts) (ft/s) 
3.0              < Time required for rotation 
2                < Print flag