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

Kentaro Hayashi, Shigeru Aso, Yasuhiro Tani

Research output: Contribution to journalArticle

61 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 languageEnglish
Pages (from-to)233-236
Number of pages4
JournalJournal of Spacecraft and Rockets
Volume43
Issue number1
DOIs
Publication statusPublished - Jan 1 2006

Fingerprint

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

Cite this

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

In: Journal of Spacecraft and Rockets, Vol. 43, No. 1, 01.01.2006, p. 233-236.

Research output: Contribution to journalArticle

Hayashi, Kentaro ; Aso, Shigeru ; Tani, Yasuhiro. / Experimental study on thermal protection system by opposing jet in supersonic flow. In: Journal of Spacecraft and Rockets. 2006 ; Vol. 43, No. 1. pp. 233-236.
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