Numerical analyses of the transonic nozzle inviscid flow and supersonic jet impingement on a jet TAB are presented.
采用数值分析方法分析了跨声速喷管无粘流动和超声速射流对挡流板的冲击流场。
Instead of the sonic nozzle, low supersonic nozzles have been utilized to solve the choking problem in transonic wind tunnel testing of high angle-of-attack and high blockage.
本文介绍用低超声速喷管代替声速喷管，解决了大迎角大堵塞度跨声速实验时的风洞壅塞问题。
FL-7 is a continuous transonic wind tunnel, which is powered by three engines. Mach number is adjusted by the rotating speed of engines, the flexible wall nozzle and the by-pass valve.
7风洞是以三台航空发动机为动力的跨音速风洞，通过调节发动机转速、柔壁及旁路活门开度来实现对M数的控制。
A numerical example for the transonic flows with shock wave in the converging-diverging square nozzle is used to indicate the effectiveness of this scheme.
作为算例，对伴有激波的方形收放喷管跨声速流动进行了计算，以显示方法的有效性。
FL-7 is a continuous transonic wind tunnel, which is powered by three engines. Mach number is adjusted by the rotating speed of engines, the flexible wall nozzle and the by-pass valve.
FL - 7风洞是以三台航空发动机为动力的跨音速风洞，通过调节发动机转速、柔壁及旁路活门开度来实现对M数的控制。
FL-7 is a continuous transonic wind tunnel, which is powered by three engines. Mach number is adjusted by the rotating speed of engines, the flexible wall nozzle and the by-pass valve.
FL - 7风洞是以三台航空发动机为动力的跨音速风洞，通过调节发动机转速、柔壁及旁路活门开度来实现对M数的控制。
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