Study of separating compressible turbulent boundary-layers

摘要: The prediction of incipient separation due to shock wave interaction with a boundary layer is critical prerequisite in the design air-breathing engine inlets and combustors. These wave/boundary interactions occur both two-dimensional three-dimensional forms. In 1970's Korkegi developed empirical correlations predict turbulent layers based on available data from other researchers. an attempt understand mechanism when subjected wave, analysis momentum arguments has been formulated compared correlations. aim this work investigate experimentally numerically suitability predictions at upper Mach number limit correlation. conditions studied are hypersonic, perfect gas 9.5. Experiments were conducted small reflected tunnel model designed produce along inner wall circular duct. Incident shocks varying strength produced by placing cones different semivertex angles centreline duct, near exit. Static pressure heat transfer rates measured duct surface. Numerically these simulated using finite volume formulation for solution compressible Navier-Stokes equations. Large-Eddy Simulation (LES) used Approximate Deconvolution Model subgrid scale (SGS) closure include effects turbulence. Reasonable agreement was observed between experimental numerical results 8°, 15° 20° cone angles. Interaction separated identified numerically. At stage selected have inconclusive determining either