Supersonic three-dimensional oscillatory piecewise continuous kernelfunction method

The three-dimensional subsonic piecewise continuous kernel function method formulated for studying oscillatory or steady flows is extended in the present work to planar supersonic wings. The work treats problems associated with the allocation of boxes on the wing, the choice of pressure polynomials, the determination of the collocation points, and the numerical integration techniques resulting from the special form of the supersonic kernel function. Results are presented which confirm the accuracy of the method and its rapid convergence characteristics.