ect Question 5 0 / 3 pts An aircraft has the CL-a curve shown in Figure 4.12. The following data applies: Weight = 20 000 lb Wing area, S = 340 sq. ft. Density altitude = 10 000 ft TAS = 242.4 kts. Find the aircraft's AOA for steady. 1.6 1.4 CLEAR 1.2 10 CL O.8 Straight portion 0.6 0.4 0.2 0 0 2 6 8 10 12 14 16 18 Angle of attack (a) Stall angle of attack Figure 4.12 G VE. AOA for a symmetrical airfoil. 2 degrees