A naturally developed turbulent boundary layer past convex corners was studied. Attention is on the transition of subsonic and transonic expansion flows. Convex-corner angle α ranges from 5 to 20 deg, and freestream Mach numbers M∞ are 0.33, 0.64, and 0.83. Reynolds numbers based on the incoming boundary-layer thickness Reδ0 are 10.0, 14.9, and 16.8 × 104, respectively. Transition of subsonic and transonic expansion-corner flow is observed at M∞2 α = 6.14. The sudden expansion near the corner is also scaled with this parameter at M∞ = 0.64 and 0.83, but not for M∞ = 0.33.
All Science Journal Classification (ASJC) codes
- Aerospace Engineering