An experimental study on transonic swept convex-corner flows

K. M. Chung, Kao Chun Su

研究成果: Article同行評審

3 引文 斯高帕斯(Scopus)


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.

頁(從 - 到)565-569
期刊Aerospace Science and Technology
出版狀態Published - 2019 1月

All Science Journal Classification (ASJC) codes

  • 航空工程


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