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ZOOM + a) If the incompressible lift coefficient for the wing of the B-2 is c = 0.9, determine the lift coefficient at M. =
ZOOM + 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 =
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