The article discusses ways in which the integrals resulting from a zero-order discontinuous pressure distribution can be arranged in such a way that they can be solved by either normal quadrature or curve fitting followed by analytical integration is shown. This ability amplifies the panel method for unsteady supersonic flow and is essential to model the discontinuities that occur in reality, e.g., at the supersonic leading or trailing edges and control surface hinge lines.
Reference:
Van Zyl, L.H. 1994. Integration of the supersonic kernel function. Journal of Aircraft, Vol. 31(6), pp. 1433-1435.
Van Zyl, L. H. (1994). Integration of the supersonic kernel function. http://hdl.handle.net/10204/2245
Van Zyl, Louwrens H "Integration of the supersonic kernel function." (1994) http://hdl.handle.net/10204/2245
Van Zyl LH. Integration of the supersonic kernel function. 1994; http://hdl.handle.net/10204/2245.
