항공역학 8장 연습문제 풀이
2, 5, 7, 11, 12, 13
2. The temperature in the reservoir of a supersonic wind tunnel is 519°R. In the test section, the flow velocity es 1385 ft/s. Calculate the test-section Mach number.
Assume the tnnel flow is adiabatic.
5. Consider the isentropic flow through a supersonic nozzle. If the test-section conditions are given by p=1 atm, T=230K, and M=2, calculate the reservoir pressure and temperature.