IMPULSE HYPERSONIC AERODYNAMIC TUNNEL Russian patent published in 2020 - IPC G01M9/02 

FIELD: experimental aerodynamics.

SUBSTANCE: device relates to the field of experimental aerodynamics, in particular to vacuum aerodynamic units of short-term action, providing modeling of flight conditions of aircrafts (AC) in upper layers of atmosphere and in outer space, and can be used to produce a hypersonic gas flow with large Mach numbers in laboratory conditions. Device comprises common channel, interconnected in series high-pressure chamber, cylindrical channel and hypersonic nozzle extending into vacuum chamber, channel shutoff means arranged between the high-pressure chamber and the cylindrical channel and between the cylindrical channel and the nozzle inlet and the recording equipment. At that, the nozzle end part is equipped with a detachable flaring fixed on it, with an inner surface which is a continuation of the nozzle surface, with channels made in the flare wall and escaping inside the flare, which volumes inside the wall are connected to each other. Volumes of channels connected to each other are connected to branch pipes located along the outer surface of the socket and the nozzle, open ends of the branch pipes are directed opposite to the flow, wherein the length of the branch pipes is related to the time of quasi-stationary efflux of the flow from the funnel and the speed of sound by the corresponding ratio.

EFFECT: technical result consists in design simplification.

1 cl, 5 dwg