Effect of Reynolds number on compressible convex-corner flows

Kung Ming Chung, Po Hsiung Chang, Keh Chin Chang

研究成果: Article同行評審

2 引文 斯高帕斯(Scopus)

摘要

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.

原文English
頁(從 - 到)443-454
頁數12
期刊Advances in Aircraft and Spacecraft Science
1
發行號4
DOIs
出版狀態Published - 2014 10月 1

All Science Journal Classification (ASJC) codes

  • 航空工程
  • 流體流動和轉移過程

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