Assume that we wish to design a Mach 10 hypersonic wind tunnelusing air as the test medium. We want the static pressure andtemperature in the test stream to be that for a standard altitudeof 55 km. Calculate (a) the exit-to-throat area ratio, (b) therequired reservoir pressure (in atm), (c) the required reservoirtemperature, and (d) the exit velocity. What do these results tellyou about the special (and sometimes severe) operating requirementsfor a hypersonic wind tunnel?
