A Mach = 2 supersonic wind tunnel is to be designed to have a 3 foot by 3 foot square test section, and will use air to be supplied from a reservoir at standard atmospheric temperature and 5 atmospheres absolute pressure. The nozzle is of constant width of 3 ft.

Using the 1-D compressible equations, determine the following:

1. 1. At the throat:
      1. height, in
      2. pressure, psia
      3. temperature, R
      4. speed of sound, ft/s
      5. flow speed, ft/s

   2. At the test section:
      1. pressure, psia
      2. temperature, R
      3. speed of sound, ft/s
      4. flow speed, ft/s

2. Redo the above using the 1-D compressible flow tables.

3. Calculate the flow rate in slug/s.

Due: April 24

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