Aerospace Engineering > GATE 2013 > Longitudinal Stability and Control
A wing-body alone configuration airplane with a wing loading of W/S = 1000 N/m2 is flying in cruise condition at a speed V = 90 m/s at sea-level (air density at sea-level ρ∞ = 1.22 kg/m3).
The zero lift pitching moment coefficient of the airplane is Cmacwb = Cm0 = –0.06
and the location of airplane aerodynamic center from the wing leading edge is Xac = 0.25c.
Here c is the chord length.
The airplane trim lift coefficient CL~win is
The airplane trim lift coefficient CL~win is
Correct : c
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