Experiments were performed to investigate a transonic, turbulent boundary layer over a bi-convex corner. The total turning angle çranged from 10 deg to 17 deg. In subsonic expansion flows, the presence of a bi-convex corner results in a decrease in local peak Mach number Mpeak and the amplitude of peak surface pressure fluctuations (σp/pw)max. There is a delay in transition from subsonic to transonic expansion flows. A dual expansion is observed in transonic expansion flows. Shock structure, boundary-layer separation and (σp/pw)maxwere dependent on freestream Mach number M, first turning angle η1and η. The length of the first corner L1also plays an important role. An increase in L1results in less flow expansion, while a decrease in the amplitude of (ηp/pw)max is associated with a shorter L1.
All Science Journal Classification (ASJC) codes
- Aerospace Engineering