Let us double the exit Mach number of the tunnel in Prob. 4.40 simply by adding a longer nozzle section with the requisite expansion ratio. Keep the reservoir properties the same as those in Prob. 4.40. Then we have a Mach 20 wind tunnel, with test-section pressure and temperature considerably lower than in Prob. 4.40; that is, the test-section flow no longer corresponds to conditions at a standard altitude of 55 km. Be that as it may, we have at least doubled the Mach number of the tunnel. Calculate (a) the exit-to-throat area ratio of the Mach 20 nozzle and (b) the exit velocity. Compare these values with those for the Mach 10 tunnel in Probs. 4.40 and 4.41. What can you say about the differences? In particular, note the exit velocities for the Mach 10 and Mach 20 tunnels. You will see that they are not much different. What is causing the big increase in exit Mach number?
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