Question #4: Assume that 1/5 scale airplane geometry, which has 1.2 m wing to wing span length, is tested at an atmospheric wind tunnel at sea level. The following measurements are taken at 0.5 Mach speed: Lift force =FL = 500 N and Pitch moment =My = 30 N.m Calculate the real aircraft force and moment values at 15,000 m altitude at 0.5 Mach velocity. (Take the reference area of the wind tunnel model as 0.3 m2)