HYPERSONIC SHOCK AERODYNAMIC PIPE Russian patent published in 2017 - IPC G01M9/02 

FIELD: physics.

SUBSTANCE: invention relates to vacuum aerodynamic installations providing modelling of aircraft flight conditions in the upper layers of the atmosphere and in outer space and can be used to obtain a hypersonic gas flow with large Mach numbers in the laboratory. The hypersonic shock wind tunnel comprises a common channel connected in series, a high pressure chamber connected in series, a cylindrical channel and a hypersonic nozzle extending into the vacuum chamber, channel shutoff means arranged between the high pressure chamber and the cylindrical channel and between the cylindrical channel and the inlet to the nozzle, and recording equipment. In this case, the end part of the nozzle is provided with channels formed in its wall and inwardly extending nozzles, the volumes of which inside the wall are connected to each other and through a controlled valve with a vacuum source higher than in the vacuum chamber.

EFFECT: increasing the reliability of data obtained in the study of hypersonic aircraft models in laboratory studies.

2 cl, 2 dwg