A study is carried out on a hypersonic inlet with rectangular-to-circular shape transition and forebody using numerical simulation and highenthalpywindtunnel test.
对一种带前体的高超声速矩转圆形进气道开展了数值仿真及高焓脉冲风洞试验研究。
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After the study, further recongniztion are done to flow characteristics of highenthalpy free piston shock wave windtunnel.