AE616 - Hypersonic Wind Tunnel And Shock Tunnel - Engineering Assignment Help

Assignment Task

Problem:

You need a hypersonic wind tunnel to test a symmetric 2-D diamond-shaped airfoil at 1 o angle of attack at Mach 8. Such high Mach numbers are difficult to obtain using a typical supersonic wind tunnel. Hence, a shock tunnel is used. A shock tunnel is nothing but a C-D nozzle attached to a shock tube. The nozzle is separated from the tube by a diaphragm which ruptures after the reflected shock generates a high pressure behind itself. The nozzle exit is followed by the test section, which is connected to a low-pressure dump tank. Refer the figure for a better idea

Assume:

1. Pressure pump for driver tube can provide up to 200 bar pressure

2. You can fill the driver tube with any gas you want

3. You can heat the driver tube gas to any temperature you want, but below 750 K.

4. Can set the dump tank to low pressure up to 10-3 bar.

5. Assume that the driver tube and dump tank are at ambient temperature, and are filled with helium (explain in the discussion, why choosing helium is a good idea for calculations).

6. Pressure behind the reflected shock will be the stagnation pressure for the C-D nozzle.

7. No dissociation, ionization, etc. high temperature effects anywhere in the flow.

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