3) Calculate the free rudder neutral point for the aircraft whose characteristics are given below. Determine its longitudinal static stability. dɛ = 0.4, 0.4, n=1.0 спос = -0.005 [1/º] (CL)=0.09 [1/º],

(c) = 0.08 [1/º], =-0.003 [1/9], da Спо = 0.0, Cha x. ac = 0.5 0.8 Xcg x 0.3, S₁ = 3.5 m² S₁ = 10 m² 0.55 0 τ 0.35 0.7 Control Surface Area Lift Surface Area