A flying-wing bomber is cruising at 15,000 meters. The wing can be approximated by a flat plate with a 2.5-meter chord and 35-meter span. If the angle of attack is 20, what is the approximate lift coefficient and wave-drag coefficient if the craft is cruising at M = 1.2 ? What are the lift and wave-drag forces acting on the wing? Solve the problem in the International system of units. cl=.2105