FIELD: wind tunnels.
SUBSTANCE: invention relates to wind tunnels and can be used for various tests of large-scale models of aircraft, incl. full-scale propellers of promising helicopters, ground transport, buildings, structures, bridges, performance of acoustic tests. Device comprises a nozzle and a diffuser, with a subsonic speed of more than 100 m/s and the presence of an acoustic chamber, includes an inlet device of the diffuser, made in the form of an annular funnel and connected by means of a bypass channel located outside the acoustic chamber, with an outlet device made in the form of an annular channel and located around the nozzle, wherein the bypass channel is equipped with adjustable valves. Through holes are made near the inlet section of the diffuser along the perimeter of its wall. Method is characterized by the fact that the diffuser is equipped with an inlet device made in the form of an annular socket, and by means of a bypass channel is connected to an outlet device made in the form of an annular channel and located around the nozzle. Bypass channel is placed outside the acoustic chamber and equipped with valves arranged inside it, which regulate the flow direction in the channel, providing an increase in the flow rate in the working part and/or replacement of heated air from the channel with cold air from the external medium.
EFFECT: reduction of energy losses, increase of flow rate in the working part, stabilization of temperature due to air exchange with the environment, reduction of pulsations of the working flow and reduction of background noise level.
3 cl, 4 dwg
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Authors
Dates
2024-09-24—Published
2024-04-23—Filed