We wish to design a Mach 3 supersonic wind tunnel, with a static pressure and temperature in
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We wish to design a Mach 3 supersonic wind tunnel, with a static pressure and temperature in the test section of \(0.1 \mathrm{~atm}\) and \(400^{\circ} \mathrm{R}\), respectively. Calculate:
a. The exit-to-throat area ratio of the nozzle
b. The ratio of diffuser throat area to nozzle throat area
c. Reservoir pressure
d. Reservoir temperature
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