Question

3. For this problem, use the following aircraft properties: Gross weight, W-20,000 lbs Wing area, S 300 ft Mean aerodynamic chord of wing. -6f CG range: Max forward: 25% MAC, Max aft: 55% MAC Aerodynamic center of wing/body is at 25% MAC Tail lift slope, a-4.5 rad Elevator effectiveness, ae 2.0 rad Wing/body lift coefficient, CLwb 5.50ab Wing/body pitching moment coefficient about aerodynamic center, Cmac wb 0.1 · · b, or σε %α-0.3 radi Tail downwash angle, ε-0.3 Aircraft drag coefficient, Co-0.02+0.05C . Tail aerodynamic center is 18 ft behind aerodynamic center of the wing/body In trimmed cruising flight, Lz W, T D The thrust line of the propulsion system is 10 inches below the CG Assume the pitching moment due to the propulsion system is constant (i.e., only a Cm.o, effect). Compute the tail area so the aircraft has a static margin of 5% with the CG at the aft-most location a.

Answer 1

this is very very similar to he question just change the numerical values

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