Accession Number:

ADA067171

Title:

A Comparison of Panel Methods for Subsonic Flow Computation,

Personal Author(s):

Corporate Author:

ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT NEUILLY-SUR-SEINE (FRANCE)

Report Date:

1979-02-01

Abstract:

Panel, or surface singularity, methods have been developed to the stage where they provide nominally exact numerical solutions for incompressible flow potential around complicated, real aircraft configurations. A large variety of these methods are in use or under development. This report provides a data base against which the various programs may be checked and makes comparisons of several methods with the datum solutions for several simple wing configurations and nacelle configurations. Datum results are from the Roberts BAe Spline-Naumann Program, and a pilot version of the Boeing Advanced Panel-Type Influence Coefficient Method. Author

Pages:

0091

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Identifiers:

Subject Categories:

Communities Of Interest:

Modernization Areas:

File Size:

30.28MB

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