Upstream disturbed boundary layer on compressible convex-corner flows

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An experimental program was conducted to investigate the upstream disturbance, which in terms of upstream blowing jet, on compressible convex corner flows. The effects of blowing rate and air injection pattern were addressed. It is found that the upstream disturbance tends to decrease the local Mach number, which results in the delay in transition of subsonic and transonic expansion flows. Upstream movement of shock wave in transonic interactions is also observed, and peak pressure fluctuations are attributed to shock oscillation. The effect of air injection pattern is more pronounced on the pressure fluctuations near the convex corner.

Original languageEnglish
Pages (from-to)1-9
Number of pages9
JournalHangkong Taikong ji Minhang Xuekan/Journal of Aeronautics, Astronautics and Aviation, Series B
Issue number1
Publication statusPublished - 2009 Dec 3

All Science Journal Classification (ASJC) codes

  • Space and Planetary Science
  • Aerospace Engineering

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