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 C_mac^wb = C_m0 = –0.06 and the location of airplane aerodynamic center from the wing leading edge is X_ac = 0.25c. Here c is the chord length.
The airplane trim lift coefficient C_L~win is