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The flow past a planar delta wing is studied for strong interaction between the boundary layer and the outer supersonic flow. The disturbance propagation in the laminar boundary layer is investigated. The characteristic surface associated with induced pressure is found. The results of the theoretical and numerical analysis of disturbance propagation under changes of the relevant parameters of the problem for three-dimensional (3D) flows are presented.

Propagation of disturbance in boundary layer on planar delta wing in the strong interaction regime