An experimental study on transonic swept convex-corner flows

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 degrees -17 degrees, respectively. The swept angle was 5 degrees-15 degrees. 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. (C) 2018 Elsevier Masson SAS. All rights reserved.