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Development of supersonic computational aerodynamic program using panel method (1987)

Maruyama, Y. ; Akishita, S. ; Nakamura, A.

In: CASI

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Publication Date: 2019-08-13

Description: An aerodynamic program for steady supersonic linearized potential flow using a higher order panel method was developed. Boundary surface is divided into planar triangular panels on each of which a linearly varying doublet and a constant or linearly varying source are distributed. Distributions of source and doublet on the panel assemblies of the panels can be determined by their strengths at nodal points, which are placed at the vertices of the panels for linear distribution or on each panel for constant distribution.

Keywords: AERODYNAMICS

Type: NASA-TT-20113 , NAS 1.77:20113

Format: text

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