Integration of the supersonic kernel function

Please use this identifier to cite or link to this item: http://hdl.handle.net/10204/2245

Title:	Integration of the supersonic kernel function
Authors:	Van Zyl, LH
Keywords:	Supersonic kernal function Integration Zero-order discontinous pressure distribution Analytical integration Supersonic flow Control surface hinge lines
Issue Date:	Nov-1994
Publisher:	American Institute of Aeronautics and Astronautics
Citation:	Van Zyl, LH. 1994. Integration of the supersonic kernel function. Journal of Aircraft, Vol. 31(6), pp. 1433-1435.
Abstract:	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.
URI:	http://hdl.handle.net/10204/2245
ISSN:	0021-8669
Appears in Collections:	Aeronautic systems General science, engineering & technology

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