Min Su HWANG, Hyoung Jin LEE

DOI Number: N/A

Conference number: HiSST-2024-318

In hypersonic flow, pressure load and heat loads occur due to a shock wave generated in front of an aircraft, and the counter-flow jet was proposed as a technique for pressure load and heat reduction. When the counter-fow jet is injected, Long Penetration Mode(LPM) and Short Penetration Mode(SPM) was observed based on the total pressure ratio of the freestream and counter-flow jet (P0j/P0f, PR). As the PR increased, a recirculation region between the shock wave and a nose of the aircraft is wider, leading to decrease in both the pressure load and the heat load. In this study, reduction of pressure load and heat load caused by the counter-flow jet on a blunt body in hypersonic flow was investigated. The experiment was conducted in the M 7.0 hypersonic shock tunnel. For measuring a heat flux on the surface of the blunt body, in-house K & E type fast response coaxial thermocouple was used. As a result of the experiment, it was confirmed that the in-house thermocouple normally measured surface temperature. When the counter-flow jet was injected, pressure and temperature on the surface of the blunt body was reduced, and the reduction effect was enhanced as the PR was higher.

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In Categories: 1.Events, High-Speed Aerodynamics and Aerothermodynamics, HiSST 2024
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