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Effect of Reynolds number on compressible convex-corner flows

  • Chung, Kung-Ming (Aerospace Science and Technology Research Center, National Cheng Kung University) ;
  • Chang, Po-Hsiung (Department of Aeronautics and Astronautics, National Cheng Kung University) ;
  • Chang, Keh-Chin (Department of Aeronautics and Astronautics, National Cheng Kung University)
  • Received : 2014.03.07
  • Accepted : 2014.05.27
  • Published : 2014.10.25
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Abstract

An experimental study was conducted to investigate the effect of Reynolds number on compressible convex-corner flows, which correspond to an upper surface of a deflected flap of an aircraft wing. The flow is naturally developed along a flat plate with two different lengths, resulting in different incoming boundary layer thicknesses or Reynolds numbers. It is found that boundary layer Reynolds number, ranging from $8.04{\times}10^4$ to $1.63{\times}10^5$, has a minor influence on flow expansion and compression near the corner apex in the transonic flow regime, but not for the subsonic expansion flow. For shock-induced separated flow, higher peak pressure fluctuations are observed at smaller Reynolds number, corresponding to the excursion phenomena and the shorter region of shock-induced boundary layer separation. An explicit correlation of separation length with deflection angle is also presented.

Keywords

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