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

Kentaro Hayashi, Shigeru Aso, Yasuhiro Tani

研究成果: ジャーナルへの寄稿記事

65 引用 (Scopus)

抄録

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.

元の言語英語
ページ(範囲)233-236
ページ数4
ジャーナルJournal of Spacecraft and Rockets
43
発行部数1
DOI
出版物ステータス出版済み - 1 1 2006

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aerodynamic heating
Aerodynamic heating
thermal protection
supersonic flow
Supersonic flow
aerodynamics
experimental study
pressure ratio
heating
flow stability
blunt bodies
Mach number
heat flux
Heat flux
Hot Temperature
protection system

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Space and Planetary Science

これを引用

Experimental study on thermal protection system by opposing jet in supersonic flow. / Hayashi, Kentaro; Aso, Shigeru; Tani, Yasuhiro.

:: Journal of Spacecraft and Rockets, 巻 43, 番号 1, 01.01.2006, p. 233-236.

研究成果: ジャーナルへの寄稿記事

Hayashi, Kentaro ; Aso, Shigeru ; Tani, Yasuhiro. / Experimental study on thermal protection system by opposing jet in supersonic flow. :: Journal of Spacecraft and Rockets. 2006 ; 巻 43, 番号 1. pp. 233-236.
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