Side-Wash Angle For an airplane with the maximum gross weight of 70,000 pounds, the differential force generated by the vertical tail's lift causes a negative rolling moment calculated at -2000 lbf-ft. The variation of side-wash angle with sideslip angle is given below in the figure. The flight condition and geometric and aerodynamic characteristics are as given below: M = 0.75, p = 0.00046 slug/ft, T = 389.97R bw = 60ft, S = 540ft Zv 13.36ft, l = 23 ft, b B = 3, = 1 = 6.346ft, Sv = 46.58ft For this problem, use the following equation for the rolling moment due to vertical tail: L = CL, ( + ) Q v Sv For the Directional stability of the airplane and good handling qualities, the value of Cn B should be between 0.06-0.15 per radian. Find out if this airplane satisfies this condition. Neglect the fuselage and wing contribution. (deg.) 4 3.5 The Variation of Side-Wash Angle with Sideslip Angle 3 2.5 2 Series 1 1.5 1 0.5 0 0 1 2 3 4 5 6 7 89 10 10 Slideslip Angle (deg.)