A nozzle for a supersonic wind tunnel is designed to achieve a Mach number of 3.0, with

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A nozzle for a supersonic wind tunnel is designed to achieve a Mach number of 3.0, with a velocity of \(2000 \mathrm{~m} / \mathrm{s}\), and a density of \(1.0 \mathrm{~kg} / \mathrm{m}^{3}\) in the test section. Find the temperature and pressure in the test section and the upstream stagnation conditions. The fluid is helium.

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