激波风洞 meaning in Chinese

shock tunnel

Preliminary experimental investigation on supersonic combustion phenomena with shocktunnel
激波风洞中超声速燃烧现象的初步实验研究
Comparisons of experimental and computational shock mach number are made for four different condition . the results of numerical simulation agree with that of experiment , show good agreement between numerical simulation results and test results
结合气动中心进行的激波风洞试验，对四组不同试验情况进行了数值模拟，给出了测量困难的温度值，数值模拟得到的结果与试验值具有较好的一致性。