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a) If the incompressible lift coefficient for the wing of the B-2 is c = 0.9, determine the lift coefficient at M = 0.7.
a) If the incompressible lift coefficient for the wing of the B-2 is c = 0.9, determine the lift coefficient at M = 0.7. b) The free-stream Mach number for the wing of the B-2 aircraft flying through the air is M = 0.7. Determine the pressure coefficient at a point on the wing where the local Mach number is M = 1.1. ZOOM +
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