Effect of Reynolds number on compressible convex-corner flows

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2 Citations (Scopus)


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 8.04×104 to 1.63×105, 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.

Original languageEnglish
Pages (from-to)443-454
Number of pages12
JournalAdvances in Aircraft and Spacecraft Science
Issue number4
Publication statusPublished - 2014 Oct 1

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Fluid Flow and Transfer Processes


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