Certain results of the numerical investigation of the possibility of controlling the structure of flow near a V-shaped wing with an opening angle greater than p under an asymmetric flow around by a supersonic stream under the regimes with shock waves attached to the leading edges or with a centered rarefaction wave on the lee console are presented.

The non-free interaction between a shock wave and the boundary layer on a swept plate set at incidence in the undisturbed flow is studied using different experimental methods including special laser techniques for visualizing supersonic conical gas flows. It is shown that under shock-layer conditions the non-free interaction can lead to conical flow breakdown before the incident shock reaches the leading edge of the plate.