Experimental study on thermal protection system by opposing jet in supersonic flow

Kentaro Hayashi; Shigeru Aso; Yasuhiro Tani

doi:10.2514/1.15332

Experimental study on thermal protection system by opposing jet in supersonic flow

Kentaro Hayashi, Shigeru Aso, Yasuhiro Tani

Space Systems Engineering

Research output: Contribution to journal › Article › peer-review

85 Citations (Scopus)

Abstract

The reduction of aerodynamic heating by opposing jet was experimentally investigated. Geometric ratio of diameters and Mach numbers were fixed, and the flow stability was determined by the total pressure ratio of freestream to opposing jet. It was observed that the reduction of aerodynamic heating caused by the opposing jet proved to be quiet effective at the nose of the blunt body. As the pressure ratio is increased, the heat flux decreases over the model surface, and remarkable reduction of aerodynamic heating was observed in nose regions at high pressure rate.

Original language	English
Pages (from-to)	233-236
Number of pages	4
Journal	Journal of Spacecraft and Rockets
Volume	43
Issue number	1
DOIs	https://doi.org/10.2514/1.15332
Publication status	Published - 2006

All Science Journal Classification (ASJC) codes

Aerospace Engineering
Space and Planetary Science

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