Effects of shock wave impingement on supersonic film cooling

Kenichi Takita, Goro Masuya

研究成果: Article査読

7 被引用数 (Scopus)

抄録

The effects of shock wave impingement on supersonic film cooling is presented. The thickness of the mixing layer of the coolant flow and of the main flow was not greatly changes by shock wave impingement, though the turbulent kinetic energy doubled behind the impingement position. This indicates that the decrease in cooling efficiency due to shock wave impingement is mainly the result of the decrease in local Mach number. An increase in the injection Mach number of a coolant extended the region where film cooling is effective in the case of no shock impingement. The increase in the injection Mach number mitigated the reduction of film cooling efficiency by shock wave impingement and reduced the interaction region.

本文言語English
ページ(範囲)602-604
ページ数3
ジャーナルJournal of Spacecraft and Rockets
36
4
DOI
出版ステータスPublished - 1999 1 1

ASJC Scopus subject areas

  • 航空宇宙工学
  • 宇宙惑星科学

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