Hypersonic wind shock tube

摘要

The invention relates to the field of experimental aerodynamics, in particular to a vacuum-blown installations providing simulation of aircraft flight conditions (aircraft) in the upper atmosphere and in space, and can be used to produce hypersonic gas stream with high Mach numbers in the laboratory.; The technical result - increasing the reliability of the data obtained in the study of models of hypersonic aircraft in the laboratory.; This result is achieved in that the hypersonic shock wind tunnel comprises forming a common channel in series between a connected high-pressure chamber, the cylinder bore and hypersonic nozzle exiting into the vacuum chamber, channel overlap means mounted between the high pressure chamber and the cylindrical channel and between the cylindrical bore 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 nozzle formed in the wall of the socket and facing inwardly of its channels, the volumes of which inside wall are connected together and via a controllable valve to a vacuum source, higher than in the vacuum chamber. 1 ZP f ly-3-yl.