The design concept and principle of injector valve system of hypersonicwindtunnel controlled by the computer are introduced in this paper.
本文介绍了高超声速风洞引射器阀门系统采用计算机控制的设计思想和原理框图。
2
A kind of scan pitot-pressure rake with water cooler was designed in IMCAS for the hypersonic propulsion windtunnel flow measurement.
笔者自行设计研制了用于高超声速推进风洞流场测量的带有水冷装置的可移动式扫描总压耙。
3
A study is carried out on a hypersonic inlet with rectangular-to-circular shape transition and forebody using numerical simulation and high enthalpy windtunnel test.