摘要
An experimental study was conducted to investigate the effect of swept angle on a compressible convex-corner flow. The freestream Mach number and the convex-corner angle were 0.64–0.89 and 10°–17° respectively. The swept angle was 5°–15°. The characteristics of a swept convex-corner flow were evaluated from the distributions of both mean and fluctuating pressures. Surface oil flow visualization was also performed to determine the length of shock-induced separated boundary layer. Shock excursion phenomenon was detected by pressure trace and the shock zero-crossing frequency was evaluated using a two-threshold method. A delay in transition from subsonic to transonic expansion flow for a swept case is observed. The effect of swept angle on peak pressure fluctuations and shock Strouhal number is evident.
| 原文 | English |
|---|---|
| 頁（從 - 到） | 565-569 |
| 頁數 | 5 |
| 期刊 | Aerospace Science and Technology |
| 卷 | 84 |
| DOIs | |
| 出版狀態 | Published - 2019 一月 1 |
指紋
All Science Journal Classification (ASJC) codes
- Aerospace Engineering
引用此文
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An experimental study on transonic swept convex-corner flows. / Chung, Kung-Ming; Su, Kao Chun.
於: Aerospace Science and Technology, 卷 84, 01.01.2019, p. 565-569.研究成果: Article
TY - JOUR
T1 - An experimental study on transonic swept convex-corner flows
AU - Chung, Kung-Ming
AU - Su, Kao Chun
PY - 2019/1/1
Y1 - 2019/1/1
N2 - An experimental study was conducted to investigate the effect of swept angle on a compressible convex-corner flow. The freestream Mach number and the convex-corner angle were 0.64–0.89 and 10°–17° respectively. The swept angle was 5°–15°. The characteristics of a swept convex-corner flow were evaluated from the distributions of both mean and fluctuating pressures. Surface oil flow visualization was also performed to determine the length of shock-induced separated boundary layer. Shock excursion phenomenon was detected by pressure trace and the shock zero-crossing frequency was evaluated using a two-threshold method. A delay in transition from subsonic to transonic expansion flow for a swept case is observed. The effect of swept angle on peak pressure fluctuations and shock Strouhal number is evident.
AB - An experimental study was conducted to investigate the effect of swept angle on a compressible convex-corner flow. The freestream Mach number and the convex-corner angle were 0.64–0.89 and 10°–17° respectively. The swept angle was 5°–15°. The characteristics of a swept convex-corner flow were evaluated from the distributions of both mean and fluctuating pressures. Surface oil flow visualization was also performed to determine the length of shock-induced separated boundary layer. Shock excursion phenomenon was detected by pressure trace and the shock zero-crossing frequency was evaluated using a two-threshold method. A delay in transition from subsonic to transonic expansion flow for a swept case is observed. The effect of swept angle on peak pressure fluctuations and shock Strouhal number is evident.
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UR - http://www.scopus.com/inward/citedby.url?scp=85056617772&partnerID=8YFLogxK
U2 - 10.1016/j.ast.2018.11.012
DO - 10.1016/j.ast.2018.11.012
M3 - Article
AN - SCOPUS:85056617772
VL - 84
SP - 565
EP - 569
JO - Aerospace Science and Technology
JF - Aerospace Science and Technology
SN - 1270-9638
ER -