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Shock hypersonic wind tunnel

机译：冲击高超音速风洞

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摘要

The invention relates to the field of experimental aerodynamics in particular to a vacuum aerodynamic settings, providing simulation conditions of aircraft flight (LA) in the upper atmosphere and outer space, and can be used for hypersonic flow of gas with high Mach numbers in the laboratory. The tube comprises forming a common channel in series between a connected chamber of high pressure, the cylindrical bore and hypersonic nozzle exiting into the vacuum chamber, means overlapping channel established between the chamber of high pressure and a cylindrical channel and between the cylindrical channel and the inlet of the nozzle, and the recording apparatus. In this case the end portion of the nozzle is provided with a fixable thereon detachable bell with an inner conical surface, which is a continuation of the surface of the nozzle made in the wall of the socket and facing inwardly of its channels, the volumes of which inside wall connected together and via a controllable valve, the actuator is connected to the output of high-frequency transducers pressure mounted in a cylindrical channel with a vacuum source, higher than in the vacuum chamber. The technical result is to increase the reliability of the data obtained in the study of hypersonic aircraft models in the laboratory. 1. ZP f-ly. 3-yl.
机译：本发明涉及实验空气动力学领域，尤其涉及一种真空空气动力学设置，提供了高空和外层空间中飞机飞行（LA）的模拟条件，可用于实验室中马赫数高的气体的超音速流动。 。该管包括在连通的高压室之间形成串联的公共通道，圆柱形孔和高超音速喷嘴进入真空室，是指在高压室和圆柱形通道之间以及圆柱形通道和高压通道之间建立的重叠通道。喷嘴的入口和记录装置。在这种情况下，喷嘴的端部设有可固定的可拆卸钟形件，该钟形件具有圆锥形的内表面，该圆锥形的表面是在插座壁中形成的，且面向喷嘴通道内部的喷嘴表面的延续。内壁通过一个可控制的阀连接在一起，并与高频传感器的输出端相连，该高频传感器的压力安装在具有真空源的圆柱形通道中，该真空源高于真空室中的真空源。技术成果是提高实验室研究高超音速飞机模型中获得的数据的可靠性。 1. ZP飞。 3-基。

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