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.
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