AIAA Journal · 1976 · 111 citations · 15 references
EngineeringAerospace EngineeringPhysicsAerodynamicsComputational Fluid DynamicsFluid DynamicsBoundary Layer FlowBoundary LayersBoundary-layer TheoryShock WavesSupersonic AerodynamicsTurbulent FlowCompressible Boundary LayersMach NumberReynolds NumberShock Wave InteractionsShock Wave-boundary Layer InteractionShock-wave InteractionSurface PressureTurbulent Boundary Layers
Two-dimensional compression corner and axisymmetric flare geometries were used in this study of shock wave interaction with a compressible turbulent boundary layer. The study was carried out at a Mach number of 2.9 and over a Reynolds number range of 10 5<Re60<107 (Re^up to 10 9). Detailed surface pressure, schlieren, and oil-flow data were obtained for several corner angles. A major finding of this study is that incipient separation is a gradual rather than an abrupt phenomenon. Incipient separation corner angles were found to be within a band of about 16°-18° and essentially independent of Reynolds number over the range studied.
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Dean R. Chapman, D. M. Kuehn, H. K. Larson · University of North Texas Digital Library (University of North Texas) · 1958 · 639 citations · Full text