Question 5 (Total 15 marks) Table Q1 gives the longitudinal stability coefficients for an F-104A fighter at Mach <0.3. All angles are measured in radians: CLO=0.833 CMD=0 CLa = 3.44 (b)

(c) (d) (e) CLM = 0.68 CMn = -1.46 Table Q1: Longitudinal Coefficients of F104A Other relevant parameters includes: (f) Сма = -0.64 m = 7,390kg S=18.6 m² b= 6.1 m Aircraft elevator effectiveness can be expressed as follow: C₁=CL₂ + C₁ua + CLn 7= 3.05 m C.G.@ 22 % 7 (a) At an equilibrium flight, at standard atmosphere at sea level, where density is p = 1.225 kg/m³, a = 0 and n = 0, appraise the speed that aircraft is flying. Analyse the Longitudinal Static Stability of the aircraft. Appraise the longitudinal Stability Margin, and Evaluate the neutral point of the CG. When the airplane returns from a mission, it is 600 kg lighter. What will be the equilibrium value of a and n in degree, assume the same speed and altitude. CM = CM₂ + CM₂a + CM₂n For the return mission, if the aircraft CG is shifted afterward, what will be the aft limit of the CG movement.