Visualization of Unsteady Behavior of Shock Waves around Supersonic Intake installed in Shock Tunnel

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5th Symposium on Integrating CFD and Experiments in Aerodynamics (October 3-5, 2012, Chofu Aerospace Center, Japan Aerospace Exploration Agency (JAXA)), Chofu, Tokyo, Japan

This paper describes unsteady behavior of shock waves around supersonic intake at Mach 2.5. The experiment carried out by small shock tunnel. Flow visualization was conducted with shadowgraph method and pressure-sensitive paint (PSP). A fast response anodized aluminum pressure-sensitive paint (AA-PSP) was used in the experiment. And to confirm the valid of experimental results, numerical calculation were performed by compressible Navier-Stokes equations with Weighted Average Flux (WAF) method and Adaptive Mesh Refinement (AMR). From the results of shock wave structures and pressure distribution, we confirmed shock waves behavior around the supersonic intake model at subcritical state. It considers occurring buzz.

形態: カラー図版あり

Physical characteristics: Original contains color illustrations

資料番号: AA0062070027

レポート番号: JAXA-SP-13-001E

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詳細情報 詳細情報について

  • CRID
    1050855511201774464
  • NII論文ID
    120006827908
  • NII書誌ID
    AA11984031
  • ISSN
    1349113X
  • Web Site
    http://id.nii.ac.jp/1696/00004129/
  • 本文言語コード
    en
  • 資料種別
    conference paper
  • データソース種別
    • IRDB
    • CiNii Articles

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