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。
The design concept and principle of injector valve system of hypersonic wind tunnel controlled by the computer are introduced in this paper.
而高超声速风洞喷管的设计和计算则对解决这一类问题具有重要的科学意义和实用价值。
The design and computation of the hypersonic nozzle have scientific and practical value to solve these problems.
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。
A kind of scan pitot-pressure rake with water cooler was designed in IMCAS for the hypersonic propulsion wind tunnel flow measurement.
本文设计了一座具有多种运行方式的高超声速大型脉冲风洞，该风洞可以采用炮风洞和激波管两种运行方式。
A hypersonic pulse tunnel is designed in this paper, which has multiple running modes based on gun tunnel and shock tube theory.
超声速风洞的起动过程涉及到湍流、激波及低亚声速和高超声速混合流动，是一个非常复杂的瞬态过程。
The starting process of wind tunnel, involving turbulence, shock wave, low subsonic and high supersonic mixing flows, is a very complex transient process.
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。
A study is carried out on a hypersonic inlet with rectangular-to-circular shape transition and forebody using numerical simulation and high enthalpy wind tunnel test.
对一种轴对称形式的高超声速飞行器全流道开展了风洞实验和数值模拟研究，分析了不同来流总压、飞行攻角全流道的流场结构和气动力特性。
This paper presents a numerical simulation of separated flow over an airfoil at large attack angles with oscillating excitations to study separation flow control over an airfoil.
实验中，自主设计了高超声速直联式风洞模拟自由来流马赫数5.3，通过测量进气道上壁面压力分布，研究了进气道开启过程的起动特性；
During experiment, a directly connected wind tunnel was independently designed to simulate a free stream Mach at 5.3, based on which the dynamic process of inlet opening was studied;
实验中，自主设计了高超声速直联式风洞模拟自由来流马赫数5.3，通过测量进气道上壁面压力分布，研究了进气道开启过程的起动特性；
During experiment, a directly connected wind tunnel was independently designed to simulate a free stream Mach at 5.3, based on which the dynamic process of inlet opening was studied;
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