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.
All Science Journal Classification (ASJC) codes
- Aerospace Engineering