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LOPAN - A low-order panel method for subsonic and supersonic flows

Published online by Cambridge University Press:  04 July 2016

T. D. Rubin
T. D. Rubin*
Affiliation:
Aerodynamics Department, Israel Aircraft Industries, Ben-Gurion Airport, Israel
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Abstract

A low-order panel method is presented for the calculation of subsonic or supersonic linear flow about general configurations. The method uses piecewise constant source, doublet and/or vorticity singularities. The internal Dirichlet boundary condition is applied, providing zero perturbation potential inside the configuration. The external Neumann boundary condition may refer to a condition on the outward conormal component of the perturbation velocity (the so-called 'linearised normal mass flux'). However, the program may, if required, proceed to obtain specified conditions on the outward normal component of the perturbation velocity, using an iterative procedure.

Type
Research Article
Information
The Aeronautical Journal , Volume 93 , Issue 925 , May 1989 , pp. 177 - 182
Copyright
Copyright © Royal Aeronautical Society 1989 

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