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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 1990, Vol. 11 ›› Issue (3): 127-131.

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MACH NUMBER EFFECTS ON UPSTREAM INFLUENCE IN SWEPT SHOCK WAVE/TURBULENT BOUNDARY LAYER INTERACTIONS

Deng Xueying, Liu Zhizhong Cut Jinhui   

  1. Beijing University of Aeronautics and Astronautics
  • Received:1988-08-25 Revised:1900-01-01 Online:1990-03-25 Published:1990-03-25

Abstract: The paper presents an experimental study of shock wave /turbulent boundary layer interactions by swept compression corners, which was carried out in G-3 supersonic blowdown wind tunnel at BU-AA. 15 models with swept back angle λ and 0°≤λ≤60°, 10°≤λ≤ 30° were tested throughout the study; the parameters used in tests were Re =2.42-2-47 ×107/m , Ma∞ = 1.79, 2.04 and 2.50. The results show that the conical or cylindrical upstream influence region appears, in the interactions for all models and Mach numbers. The boundary between the conical and cylindrical region varies with Ma∞, and can be physically determined by the shape of the inviscid shock wave.

Key words: shock wave, turbulent boundary layer, flow visualization