TY - JOUR
T1 - Effect of Reynolds number on compressible convex-corner flows
AU - Chung, Kung Ming
AU - Chang, Po Hsiung
AU - Chang, Keh Chin
N1 - Funding Information:
The research described in this paper was financially supported by the Ministry of Science and Technology. The authors are also grateful to the ASTRC/NCKU technical staffs for their technical support.
Publisher Copyright:
© 2014 Techno-Press, Ltd.
PY - 2014/10/1
Y1 - 2014/10/1
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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U2 - 10.12989/aas.2014.1.4.443
DO - 10.12989/aas.2014.1.4.443
M3 - Article
AN - SCOPUS:84928545246
VL - 1
SP - 443
EP - 454
JO - Advances in Aircraft and Spacecraft Science
JF - Advances in Aircraft and Spacecraft Science
SN - 2287-528X
IS - 4
ER -