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

研究成果: Paper査読

5 被引用数 (Scopus)

抄録

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.

本文言語English
DOI
出版ステータスPublished - 2012
イベント50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition - Nashville, TN, United States
継続期間: 2012 1月 92012 1月 12

Other

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

ASJC Scopus subject areas

  • 航空宇宙工学

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