Fluid Mechanics

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A supersonic wind tunnel is to be operated at M=2.2 in the test section. Upstream from the test section, the nozzle throat area is 0.07 m². Air is supplied at stagnation conditions of 500 K and 1.0 MPa (abs). At one flow condition, while the tunnel is being brought up to speed, a normal shock stands at the nozzle exit plane. The flow is steady. For this “starting” condition, immediately downstream from the shock find (a) the Mach number, (b) the static pressure, (c) the stagnation pressure, (d) the minimum area theoretically possible for the second throat downstream from the test section.

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