Computation of surface heat transfer rate on apollo CM test model in free-piston shock tunnel HIEST

Tomoaki Ishihara, Yousuke Ogino, Keisuke Sawada, Hideyuki Tanno

Research output: Contribution to conferencePaperpeer-review

5 Citations (Scopus)

Abstract

Aeroheating on the Apollo CM test model placed in the free-piston shock tunnel HI- EST was measured. The obtained heat flux distributions were reasonably correlated when normalized by a product of Stanton number and the square-root of the Reynolds number for lower to moderate total enthalpy. However, for higher total enthalpy conditions, the heat flux distributions 40-50% higher than those for other results conducted at lower total enthalpy. To clarify the possible causes of this phenomenon, we attempted to calculate heat flux around the Apollo CM test model. Obtained total heat flux considering radiated emission from driver gas agree well with measured heat ux.

Original languageEnglish
DOIs
Publication statusPublished - 2012 Dec 1
Event50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition - Nashville, TN, United States
Duration: 2012 Jan 92012 Jan 12

Other

Other50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition
CountryUnited States
CityNashville, TN
Period12/1/912/1/12

ASJC Scopus subject areas

  • Aerospace Engineering

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