Report presents the results of experimental and theoretical research conducted on flow separation associated with steps, bases, compression corners, curved surfaces, shock-wave boundary-layer reflections, and configurations producing leading-edge separation. Results were obtained from pressure-distribution measurements, shadowgraph observations, high-speed motion pictures, and oil-film studies. The maximum scope of measurement encompassed Mach numbers between 0.4 and 3.6, and length Reynolds numbers between 4,000 and 5,000,000.

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Investigation of separated flows in supersonic and subsonic streams with emphasis on the effect of transition

Interactions between shock waves and turbulent boundary layers

A finite-difference solution to the problem of the interaction between an impinging shock wave and the laminar boundary layer on a flat plate is presented. The boundary-layer equations are used to calculate the flow with the Prandtl-Meyer formula being used to determine the pressure. Two different methods for calculating the region of separated flow are discussed. Comparisons between this theory and experimental results show good agreement. The effects of the viscosity and heat-conduction relationships on the calculated results are determined. Diagrams show the influence of the Mach number and the displacement thickness of the boundary layer at the start of the interaction on the pressure distribution. The insulated plate and the plate with given temperature are considered.

The interaction of a shock wave with a laminar boundary layer

Introduction to shock-induced separation and its prevention by design and boundary layer control

: A study is presented of the characteristics of transitional and turbulent layers, and regions of shock wave-turbulent boundary layer interaction in high Reynolds number hypersonic flow. An examination and correlation of skin friction, heat transfer and pressure measurements in laminar, transitional and turbulent boundary layers on sharp flat plates and cones are presented for the Mach range from 3 to 13 at wall-to-free stream temperature ratios from 0.1 to 0. 4.

Shock Wave Turbulent Boundary Layer Interaction in Hypersonic Flow

An account is given of an investigation into the interaction between the boundary layer on a flat plate and a shock wave produced either externally, by a wedge in the supersonic main-stream, or from within the boundary layer, by a wedge held in contact with the plate. A wide range of free-stream Mach numbers, boundary-layer Reynolds numbers, and shock strengths has been covered, shock strength being defined as the ratio of the static pressure downstream of the shock to the static pressure upstream of it. Variations in these parameters can have large effects on the interaction, and there are also large differences between cases with externally generated shocks and cases where the shock is generated from within the boundary layer. The investigation has thrown light on the physical mechanisms involved. It is found that many of the major features of the interaction arise because the boundary layer separates from the surface ahead of the shock wave. The conditions under which separation occurs and the behaviour of the separated boundary layer thus have important effects, in terms of which, for example, the differences between the interactions observed with laminar and with turbulent boundary layers may be explained.

G. E. Gadd

Papers

An Experimental Investigation of the Interaction between Shock Waves and Boundary Layers