4- Consider an airplane. For this airplane the zero-lift angle of attack is -1.5, the lift slope (ao) of the airfoil section is 0.112 per degree, the lift efficiency factor t = 0.04, and the wing aspect ratio is 10. At the cruising condition the lift coefficient of the airplane is CL=0.24. a) Calculate the angle of attack of the airplane. 8P b) Calculate the lift coefficient values at 3 and 6 and draw lift coefficient - angle of attack (CL - ) curve using all available/obtained CL values. 8P