Computation of aerodynamic characteristics of finite wings in steady supersonic flow

The calculation of aerodynamic characteristics of wings based on linearised supersonic theory has been a subject of investigation for the last two decades. Practically all the methods are essentially based on discretising the fundamental integral equation connecting the velocity perturbation potential with the downwash on the wing13; and the diaphragm region. Having made a critical survey of the available methods, we have adopted an approach based on the work of Fenain which seems to be attractive from the point of view of accuracy and memory requirements. The method is rather general in the sense that the leading edges can be subsonic, sonic pr supersonic. A computer 13; programme has been developed to calculate lift, moment and wave drag coefficients for certain specific configurations including delta wings and deltawings with ailerons. Comparisons are given for a standard configuration for the steady case with other methods of Woodward, Middleton and Carlson and of conical flow theory