A blow down supersonic wind tunnel has a test section area of 0.2 m2 and a design Mach number of 2.5. The pressure and temperature in the high pressure air tank is 50 MPa and 400 K. Ignore all losses...
A blow down supersonic wind tunnel has a test section area of 0.2 m2 and a design Mach number of 2.5. The pressure and temperature in the high pressure air tank is 50 MPa and 400 K. Ignore all losses between the high pressure tank and the test section.
a) Estimate the throat area of the nozzle.
b) Estimate the static pressure and static temperature in the test
section.
c) Estimate the required gas temperature in the high pressure tank
to achieve 298 K
temperature in the test section.
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A blow down supersonic wind tunnel has a test section area of 0.2 m2 and a design Mach number of 2.5. The pressure and temperature in the high pressure air tank is 50 MPa and 400 K. Ignore all losses...
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> Hello: There is a calculation mistake in part (a) of the question. You have written the formula correctly, but the calculations are incorrect.
ALI8193 Tue, May 11, 2021 6:39 AM