Reflection Of A Weak Shock Wave From A Boundary Layer Along A Flat Plate PDF Download

This paper is concerned with the phenomena encountered when a plane oblique shock wave is incident upon the boundary layer of a flat plate. In an effort to simplify the problem, the flow field was divided into a viscous layer near the wall and a supersonic potential outer flow. The pressure disturbances due to the incident wave would be propagated upstream and downstream in the subsonic portion of the boundary layer, thus giving rise to perturbations of the boundary layer. By restricting the study to infinitesimal incident compression waves, only small perturbations were encountered and hence the ordinary linearized theory could be applied to the outer flow. In the laminar case, the boundary-layer treatment was based upon a momentum-integral equation previously derived by Howarth. The two flows must be compatible; hence, the deflection of the streamlines near the boundary layer was expressed in terms of the vertical velocity component along the edge of the boundary layer and this relation was used as a boundary condition for the outer flow. The boundary condtion determined the form of solution upstream and downstream of the point of incidence. Determination of the constants of integration was accomplished by a consideration of conditions at infinity and a matching of the two flows at the point of incidence.