極超音速流中のランプ誘起衝撃波／遷移境界層干渉の実験的研究

• 井藤 創

  防衛大学校システム工学群航空宇宙工学科

• 樫部 泰平

  防衛大学校理工学研究科

書誌事項

タイトル別名

• An Experimental Study on a Ramp-Induced Shock-Wave/Transitional-Boundary-Layer Interaction in Hypersonic Flow
• ゴク チョウオンソクリュウ チュウ ノ ランプ ユウキ ショウゲキハ センイ キョウカイソウ カンショウ ノ ジッケンテキ ケンキュウ

抄録

An experimental investigation of a shock-wave/transitional-boundary-layer interaction was conducted on a flat plate with an aft-mounted ramp in a hypersonic gun tunnel. Test Mach number was 10, the Reynolds number range Re_L based on the model plate length was from 1.1 to 3.2 × 10⁵, the attack angle of the model was zero, and the ramp deflection angle θ_w was varied from 10 to 30deg in increments of 2. The effects of Re_L and θ_w on the characteristics of the interaction region were investigated through both schlieren visualization and heat transfer measurement. The state of reattaching boundary layers were determined from these data. The following is obtained. A model that describes how the upstream influence of a shock-wave/boundary-layer interaction scales with the parameters of the incoming flow agrees with laminar data at small Re_L^-1/8Δθ_w, where Δθ_w is the incremental angle after incipient separation. The slope of the characteristic curve of the upstream influence is dependent on the type of the interaction. Re_L^-1/8 Δθ_w where the deviation from the model occurs and flow unsteadiness appears is found to become small with increasing Re_L.

収録刊行物

• 日本航空宇宙学会論文集

  日本航空宇宙学会論文集 55 (646), 541-545, 2007

  一般社団法人 日本航空宇宙学会

キーワード

• Hypersonics
• Shock-Wave/Boundary-Layer Interaction
• Transition
• Upstream Influence
• Aerodynamic Heating

詳細情報

• CRID: 1390282679447318784
• NII論文ID: 10021152588
• NII書誌ID: AA11307372
• DOI: 10.2322/jjsass.55.541
• ISSN: 24323691
• ISSN: 13446460
• NDL書誌ID: 9271895
• Web Site: https://ndlsearch.ndl.go.jp/books/R000000004-I9271895
• Web Site: https://www.jstage.jst.go.jp/article/jjsass/55/646/55_646_541/_pdf
• 本文言語コード: ja
• データソース種別:
  • JaLC
  • NDL
  • Crossref
  • CiNii Articles
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