極超音速におけるデルタ翼・球頭円柱間の空力干渉流れ場 Aerodynamic Interaction between Delta Wing and Hemisphere-Cylinder in Hypersonic Flow

この論文にアクセスする

この論文をさがす

著者

抄録

The aerodynamic interaction flow field between a delta wing and a hemisphere-cylinder modeling TSTO (Two Stage To Orbit) in hypersonic flow has been investigated. The paint method for visualization has been improved in order to perform temperature distribution measurements by the Temperature Sensitive Paint (TSP) method, where pressure sensitivity has been reduced by recoating a transparent acrylic paint. The flow field is made complicated by both shock/shock interaction and shock/boundary layer interaction. On the hemisphere-cylinder, the maximum heat flux becomes about 2.7 times as large as the stagnation heat flux in the case of a hemisphere-cylinder alone. On the other hand, the same amount of heat flux as that stagnation value is produced on the delta wing located below the tip of the hemisphere-cylinder.

収録刊行物

  • 日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences

    日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences 52(606), 289-294, 2004-07-05

    一般社団法人 日本航空宇宙学会

参考文献:  19件中 1-19件 を表示

被引用文献:  4件中 1-4件 を表示

各種コード

  • NII論文ID(NAID)
    10013338431
  • NII書誌ID(NCID)
    AA11307372
  • 本文言語コード
    JPN
  • 資料種別
    ART
  • ISSN
    13446460
  • NDL 記事登録ID
    7035515
  • NDL 雑誌分類
    ZN25(科学技術--運輸工学--航空機・ロケット)
  • NDL 請求記号
    Z74-B503
  • データ提供元
    CJP書誌  CJP引用  NDL  J-STAGE 
ページトップへ