Upstream disturbed boundary layer on compressible convex-corner flows

研究成果: Article同行評審

摘要

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.

原文English
頁(從 - 到)1-9
頁數9
期刊Hangkong Taikong ji Minhang Xuekan/Journal of Aeronautics, Astronautics and Aviation, Series B
41
發行號1
出版狀態Published - 2009

All Science Journal Classification (ASJC) codes

  • 航空工程
  • 空間與行星科學

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