Jet-Wing Interaction Flow Field Study for Missiles in Supersonic Free Streams

The flow field structure of the lateral jet flow ejected into supersonic free stream over missile bodies with and without X-shape front wings is numerically studied. Results of seven jet exit locations for two geometries are analyzed and compared. The interaction between jet flow and front wings contributes several favorable factors for maneuvering control namely the wraparound effect obstruction, another high pressure region behind the wake and extra advantaged interaction force on wings.