Effect of Reynolds number on compressible convex-corner flows

Kung Ming Chung; Po Hsiung Chang; Keh Chin Chang

doi:10.12989/aas.2014.1.4.443

Effect of Reynolds number on compressible convex-corner flows

Kung Ming Chung, Po Hsiung Chang, Keh Chin Chang

Research output: Contribution to journal › Article › peer-review

2 Citations (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 language	English
Pages (from-to)	443-454
Number of pages	12
Journal	Advances in Aircraft and Spacecraft Science
Volume	1
Issue number	4
DOIs	https://doi.org/10.12989/aas.2014.1.4.443
Publication status	Published - 2014 Oct 1

All Science Journal Classification (ASJC) codes

Aerospace Engineering
Fluid Flow and Transfer Processes

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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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T1 - Effect of Reynolds number on compressible convex-corner flows

AU - Chung, Kung Ming

AU - Chang, Po Hsiung

AU - Chang, Keh Chin

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N2 - 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.

AB - 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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