Calculate (a) the exit-to-throat area ratio, (b) the required reservoir pressure (in ), and (c) the required reservoir temperature.

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Calculate the exit velocity of the hypersonic tunnel in Prob. 4.40. Prob. 4.40. In Sec. 4.9 we defined hypersonic :flow as that :flow where the Mach number is 5 or greater. Wind tunnels with a test-section Mach number of 5 or greater are called hypersonic wind tunnels. From Eq. (4.88), the exit-to-throat area ratio for supersonic exit Mach numbers increases as the exit Mach number increases. For hypersonic Mach numbers, the exit-to-throat ratio becomes extremely large, so hypersonic wind tunnels are designed with long, high-expansion-ratio nozzles. In this and the following problems, we examine some special characteristics of hypersonic wind tunnels. Assume that wish to design a Mach 10 hypersonic wind tunnel using air as the test medium. We want the static pressure and temperature in the test stream to be that for a standard altitude of 55 km. Calculate (a) the exit-to-throat area ratio, (b) the required reservoir pressure (in ), and (c) the required reservoir temperature. Examine these results. What do they tell you about the special (and sometimes severe) operating requirements for a hypersonic wind tunnel? . TODAY AND GET AN AMAZING DISCOUNT The post Calculate (a) the exit-to-throat area ratio, (b) the required reservoir pressure (in ), and (c) the required reservoir temperature. appeared first on Term Paper Tutors.”Do you need a similar assignment done for you from scratch? We have qualified writers to help you with a guaranteed plagiarism-free A+ quality paper.