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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