Abstract
A three-dimensional (3D) structure of a separated flow in a compression corner at a free-stream Mach number M = 6 is studied. The model is a flat plate with an almost sharp leading edge on which a 30° ramp is mounted. The spanwise size of the model is equal to the length of the plate from the leading edge to the ramp. The angle of attack is varied from 0° to 15°. The shock wave structure of the flow near the model is shown. The existence of a thin high total pressure layer (dynamic layer) is found. The dynamic layer is located above the boundary layer on the ramp, downstream from the reattachment line. The existence streamwise vortices near the reattachment line is shown. The measured spectra of the wall pressure fluctuations in the reattachment region are presented.
Highlights
A supersonic §ow with a separation region near the ramp is a canonical problem involving the interaction of shock waves with the boundary layer
At a high free-stream Mach number, the shock waves are formed over the separation zone and give rise to a complex shock-wave structure that aects the downstream evolution of §ow characteristics behind the shear-layer reattachment line
The shear layer enclosing the separation zone Z is denoted by SL1
Summary
A supersonic §ow with a separation region near the ramp is a canonical problem involving the interaction of shock waves with the boundary layer (see, e. g. [1 7]). A supersonic §ow with a separation region near the ramp is a canonical problem involving the interaction of shock waves with the boundary layer At a high free-stream Mach number, the shock waves are formed over the separation zone and give rise to a complex shock-wave structure that aects the downstream evolution of §ow characteristics behind the shear-layer reattachment line. The goal of the present investigation is to clarify the 3D §ow structure eects on the distribution of the mean and §uctuating §ow characteristics near the model surface. Results of a complex experimental study of the separated §ow structure at high supersonic §ow velocities are required for veri¦cation of numerical calculations. Results of an experimental and numerical study of the 3D laminar separated §ow at a ramp for various angles of attack are reported. The study comprised a Schlieren and oil visualization of the §ow, measurement of the wall pressure, and registration of wall-pressure §uctuations at a point located on the ramp surface near the §ow reattachment
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