Effect of Reynolds number on compressible convex-corner flows

Research output: Contribution to journalArticle

1 Citation (Scopus)

Abstract

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
Volume1
Issue number4
DOIs
Publication statusPublished - 2014 Oct 1

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Reynolds number
Boundary layers
Transonic flow

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Fluid Flow and Transfer Processes

Cite this

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abstract = "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.",
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Effect of Reynolds number on compressible convex-corner flows. / Chung, Kung Ming; Chang, Po Hsiung; Chang, Keh Chin.

In: Advances in Aircraft and Spacecraft Science, Vol. 1, No. 4, 01.10.2014, p. 443-454.

Research output: Contribution to journalArticle

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