2 Aerodynamics
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Fig. 2.93 Shock waves interacting with the boundary layer
temperature along the flow direction. If the wall boundary layer is encountered, the effect of shock wave is similar to imposing a sudden inverse
pressure gradient on the boundary layer, which will seriously change the
flow characteristics of the boundary layer. If the shock wave is strong, the
interference between the shock wave and the boundary layer will cause the
separation of the boundary layer behind the wave, at the same time, it will
cause strong unsteady flow and strong heat conduction in the local area,
which will seriously affect the performance of the aircraft. Therefore, the
study of the interaction mechanism between shock wave and boundary
layer is of great significance to the prediction of transition position, separation position, shock oscillation control, separation control, and other
complex problems.
For the flow around the supersonic object, the flow outside the
boundary layer is supersonic flow, but the fluid velocity in the boundary
layer is rapidly reduced to zero velocity on the wall due to the influence