Near-field supersonic flow pattern of slender delta wings

Abstract

There is a particular need for developing analytical methods that are capable of accurately predicting the near-field flow pattern about arbitrary aircraft configuration for design optimization in connection with sonic boom as well as performance of the vehicle. Analytical studies provide a tool for understanding the near-field effects of the variations in the shape of the aircraft configuration. In the present work the theory of linearized conical flow has been applied to calculate pressure distributions over slender delta wings and at points in the field away from the wings. The present study also gives linearized results of the variations of some of the important wing parameters. Near-field flow patterns due to both first and second order conical flow fields around delta wings have been worked out. Slender delta wings with constant angle of attack, camber and thickness distribution along the span have been considered. Whitham's quasilinear approach is used for these slender delta wings to obtain a first-order uniformly valid solution. All these results are compared with those obtained from the equivalent body theory and significant differences are observed in the near-field region. Since a complete flow pattern is given the present work may be used for other aerodynamic applications.