The exit section of a convergent-divergent nozzle is to be used for the test section of a supersonic wind tunnel. If the absolute pressure in the test section is to be 140 kPa, what pressure is required in the reservoir to produce a Mach number of 5 in the test section? For the air temperature to be −20°C in the test section, what temperature is required in the reservoir? What ratio of throat area to test section area is required to meet these conditions?
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