Micro-vortex generators on transonic convex-corner flow

Kung Ming Chung, Kao Chun Su, Keh Chin Chang

研究成果: Article同行評審

3 引文 斯高帕斯(Scopus)

摘要

A convex corner models the upper surface of a deflected flap and shock-induced boundary layer separation occurs at transonic speeds. This study uses micro-vortex generators (MVGs) for flow control. An array of MVGs (counter-rotating vane type, ramp type and co-rotating vane type) with a height of 20% of the thickness of the incoming boundary layer is installed upstream of a convex corner. The surface pressure distributions are similar regardless of the presence of MVGs. They show mild upstream expansion, a strong favorable pressure gradient near the corner’s apex and downstream compression. A corrugated surface oil flow pattern is observed in the presence of MVGs and there is an onset of compression moving downstream. The counter-rotating vane type MVGs produce a greater reduction in peak pressure fluctuations and the ramp type decreases the separation length. The presence of MVGs stabilizes the shock and shock oscillation is damped.

原文English
文章編號268
期刊Aerospace
8
發行號9
DOIs
出版狀態Published - 2021 9月

All Science Journal Classification (ASJC) codes

  • 航空工程

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