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 | |
| Publication status | Published - 2014 Oct 1 |
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All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Fluid Flow and Transfer Processes
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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 journal › Article
TY - JOUR
T1 - Effect of Reynolds number on compressible convex-corner flows
AU - Chung, Kung Ming
AU - Chang, Po Hsiung
AU - Chang, Keh Chin
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.
UR - http://www.scopus.com/inward/record.url?scp=84928545246&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=84928545246&partnerID=8YFLogxK
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 -