If the angle of attack is 10, determine the section lift coefficient from Appendix D in your textbook for incompressible flow. If the Cirrus aircraft is cruising in the compressible flow regime at Mach = 0.4, determine the section lift coefficient. If the wing area is 195 f2, and the Cirrus Jet is cruising at a standard altitude of 25,000 feet, estimate the lift generated using the section lift coefficient for compressible flow. Solve the problem in the British system of units