An airplane is flying straight and level (lift = weight = 213 kN). The planform area is 650 ft 2 and the wingspan is 80 ft. The flight speed is 195 m/s. The altitude is 10,000 m where the standard conditions are T = -223 K, P = 25.5 kN/m 2 , and = 0.4135 kg/m 3 . The airfoil sections are NACA 2412 with a finite angle trailing edge. The chord distribution is elliptic. Find free stream dynamic pressure, qinf