傾斜前面円柱先頭形状によるTSTO極超音速空力干渉の低減 Reduction of TSTO Hypersonic Aerodynamic Interactions Due to Diagonally-Cut Circular Cylinder Orbiter Nose

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To make space activities more brisk, TSTO (Two Stage To Orbit) has been investigated worldwide as an advanced space transportation system. TSTO vehicles, which have a booster and an orbiter, have to make flight in a wide range of flight speed from subsonic to hypersonic, where they undergo aerodynamic interactions due to their combined bodies. In hypersonic flow regime, aerodynamic heating is critical, which depends on aerodynamic interaction pattern. In the present study, a delta-wing is employed as a booster and a diagonally-cut circular cylinder as an orbiter to reduce the aerodynamic interaction between these two bodies. It was found as a result of experiment that the heat flux on the head part of the diagonally-cut circular cylinder becomes about 2.4 times as large as the stagnation heat flux, while that on the delta-wing becomes about 0.5 times as large. These two values are roughly half of those in the case of a baseline combination: hemisphere-cylinder and delta-wing, which suggests that the diagonally-cut circular cylinder is promising as an orbiter head shape.

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  • 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 56(648), 8-14, 2008-01-05 

    日本航空宇宙学会

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各種コード

  • NII論文ID(NAID)
    10021152779
  • 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
    9351608
  • 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  IR  J-STAGE 
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