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学術誌査読

121 被引用数 (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.

本文言語英語
ページ(範囲)233-236
ページ数4
ジャーナルJournal of Spacecraft and Rockets
43
1
DOI
出版ステータス出版済み - 2006

!!!All Science Journal Classification (ASJC) codes

  • 航空宇宙工学
  • 宇宙惑星科学

フィンガープリント

「Experimental study on thermal protection system by opposing jet in supersonic flow」の研究トピックを掘り下げます。これらがまとまってユニークなフィンガープリントを構成します。

引用スタイル