Calculations were performed to investigate the supersonic flow of a turbulent boundary layer over short regions of concave surface curvature. Upstream of each curved surface the freestream Mach number was 2.9. Three different constant radii of curvature models were investigated to cover a range of curvatures and turning angles. The numerical technique solved the full, Reynolds-averaged Navier-Stokes equations using two different turbulence models: algebraic eddy viscosity model and a one-equation model. The calculations were compared with recent experimental data and the agreement was surprisingly good, especially for the computations using the one-equation model.
All Science Journal Classification (ASJC) codes
- Aerospace Engineering