T HE present work describes a theoretical simulation of the effects of a vortex generator row ahead of a shock/boundary-layer interaction zone. The row is represented by parameters characterizing the Law of the Wall/Law of the Wake structure of the turbulent boundary layer. This model is then integrated into a previously developed twodimensional computational code that utilizes an appropriate triple-deck theory of a nonseparating shock/bbundary-layer interaction. The results imply that the shape factor reduction effect associated with a vortex generator can have powerful, favorable effects on the local and overall interactive properties, but can also promote earlier incipient separation in the immediate vicinity of the shock foot. ContentsThe influence of shock/boundary-layer interaction on a supercritical wing can extend significantly downstream within the boundary layer and thus adversely affect global aerodynamic properties. This negative influence may be reduced by means of the boundary-layer control device known as the vortex generator, which delays separation by promoting mixing between the freestream and the boundary layer. The present paper describes a method that computationally simulates the gross spanwise-averaged two-dimensional effects of a vortex generator row located ahead of an unseparated shock/boundary-layer interaction zone such as that found on a supercritical wing (see Fig. 1). The model of this situation is based on fundamental Law of the Wall/Law of the Wake relations for the incoming turbulent boundary layer, combined with a triple-deck theory of the subsequent interaction zone.

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