항공역학 7장 연습문제 풀이
3, 8, 9
3. just upstream of a shock wave, the air temperature and pressure are 288 K and 1 atm, respectively; just downstream of the wave, the air temperature and pressure are 690 K and 8.656 atm, respectively. Calculate the changes in enthalpy, internal energy, and entropy across the wave.
8. In the reservoir of a supersonic wind tunnel, the velocity is negligible, and the temperature is 1000K. The temperature at the nozzle exit is 600K. Assuming adiabatic flow through the nozzle, calculate the velocity at that point.