Engineering, 19.02.2020 23:01 karli3065

Supersonic wind tunnels use a reservoir tank (or stagnation chamber) at high pressures, as there is not enough stagnation pressure or temperature in ambient air to achieve high speeds in the test section. You are to specify some parameters for a new supersonic wind tunnel. You need Mach 2.5 flow in the test section at simulated pressure and temperature of 10,000 ft standard altitude. The test section cross-sectional area is a 9 inch x 9 inch square.

Assuming you’re flowing air, determine the following:

a. Assuming choked flow, what nozzle throat area is needed to attain Mach 2.5 in the test section?

b. What reservoir pressure and temperature are required?

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Supersonic wind tunnels use a reservoir tank (or stagnation chamber) at high pressures, as there is...