Effects of shock wave impingement on supersonic film cooling

Kenichi Takita, Goro Masuya

Research output: Contribution to journalArticlepeer-review

5 Citations (Scopus)

Abstract

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.

Original languageEnglish
Pages (from-to)602-604
Number of pages3
JournalJournal of Spacecraft and Rockets
Volume36
Issue number4
DOIs
Publication statusPublished - 1999 Jan 1

ASJC Scopus subject areas

  • Aerospace Engineering
  • Space and Planetary Science

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