Japan Aerospace Exploration Agency Institute of Aerospace Technology
Japan Aerospace Exploration Agency Institute of Space and Astronautical Science
Japan Aerospace Exploration Agency Institute of Space and Astronautical Science
出版者
宇宙航空研究開発機構
出版者（英）
Japan Aerospace Exploration Agency (JAXA)
雑誌名
宇宙航空研究開発機構特別資料: 航空宇宙数値シミュレーション技術シンポジウム2006論文集
雑誌名(英)
JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2006
巻
JAXA-SP-06-010
ページ
139 - 144
発行年
2006-12-01
抄録（英）
Computations of opposing jet flow from the vertical landing rocket vehicle are performed by using Large Eddy Simulation technique. Calculated results are presented for the cases with and without jet ejection respectively, and are compared with experimental data obtained by several wind tunnel testings for the purpose of code validation. For the case without jet ejection, it is shown that dominant mean flow structures around the model are nearly reproduced in this calculation. Calculated time-averaged pressure coefficient distribution duplicates well with that of measured. For the case with jet ejection, although a quantitative agreement of measured pressure coefficient values with those given by the present calculation is yet to be accomplished, the general trend in the measured pressure coefficient distributions was reproduced well in the present calculation. It is also found that calculated characteristics of power spectrum density of pressure coefficient are similar to those of measured for the case with jet ejection.
再使用型垂直離着陸ロケットの着陸前逆噴射の数値解析
63154026.pdf
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