Calculation of intermediate hypersonic flow using multi-temperature model

Michiko Furudate, Toshiyuki Suzuki, Keisuke Sawada

研究成果: Paper査読

2 被引用数 (Scopus)

抄録

Our previous study revealed that the existing two-temperature model reasonably well reproduced the shock stand-off distance for a sphere in the intermediate hypersonic range, except for the cases where chemical reactions were almost frozen but vibrationally highly excited. In order to explain the cause of distinction, a four-temperature description of the intermediate hypersonic flowfield has been attempted. The model assigns a translational temperature and three different vibrational temperatures, one for each of three molecular species, O2, N2, and NO. Calculated shock stand-off distances for several conditions, for which the discrepancy was seen in the two-temperature calculation, are compared with the corresponding experimental data measured with a ballistic range and the calculated results using a two-temperature model. The agreement, however, is only slightly improved by the use of the present four-temperature model. A possible explanation of the modest improvement is indicated.

本文言語English
出版ステータスPublished - 2000 12月 1
イベント38th Aerospace Sciences Meeting and Exhibit 2000 - Reno, NV, United States
継続期間: 2000 1月 102000 1月 13

Other

Other38th Aerospace Sciences Meeting and Exhibit 2000
国/地域United States
CityReno, NV
Period00/1/1000/1/13

ASJC Scopus subject areas

  • 宇宙惑星科学
  • 航空宇宙工学

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