A119 制御舵面を過ぎる極超音速流の挙動

DOI

書誌事項

タイトル別名
  • Behaviour of Hypersonic Flow past a Control Flap

抄録

Understanding of hypersonic viscous interaction phenomenon over control surfaces is of particular impor-tance for designers of hypersonic vehicles. An experimental study of the behaviour of hypersonic flow past flaps is presented in this report. Impulsive glow discharge technique and Schlieren visualization using high speed video camera are applied to examining the structure upstream of the hinge. These experiments are conducted in a hypersonic gun tunnel at Mach number 10 and at Reynolds numbers based on the chord length ranging 0.8 - 2.12 × 105. The flap deflection angles studied are in the range from 0 to 0.523 rad at zero incidence. Numerical simulations based on the Navier-Stokes equations are also performed. Time lines obtained by the dis-charge technique are reasonable and the structure evaluated by the time lines correlates well with those through Schlieren and computational results. Normalized upstream influence increases with increasing Reynolds number and increasing flap angle in the range studied.

収録刊行物

キーワード

詳細情報 詳細情報について

  • CRID
    1390001204618881152
  • NII論文ID
    130003650349
  • DOI
    10.3154/jvs.25.supplement2_71
  • ISSN
    1884037X
    09164731
  • 本文言語コード
    ja
  • データソース種別
    • JaLC
    • Crossref
    • CiNii Articles
  • 抄録ライセンスフラグ
    使用不可

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