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Advanced panel-type influence coefficient methods applied to subsonic flowsAn advanced technique for solving the linear integral equations of three-dimensional subsonic potential flows (steady, inviscid, irrotational and incompressible) about arbitrary configurations is presented. It involves assembling select, logically consistent networks whose construction comprises four tasks, which are described in detail: surface geometry definition; singularity strength definition; control point and boundary condition specification; and calculation of induced potential or velocity. The technique is applied to seven wing examples approached by four network types: source/analysis, doublet/analysis, source/design, and doublet/design. The results demonstrate the forgiveness of the model to irregular paneling and the practicality of combined analysis/design boundary conditions. The appearance of doublet strength mismatch is a valuable indicator of locally inadequate paneling.
Document ID
19750036189
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Johnson, F. T.
Rubbert, P. E.
(Boeing Commercial Airplane Co. Seattle, Wash., United States)
Date Acquired
August 8, 2013
Publication Date
January 1, 1975
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 75-50
Meeting Information
Meeting: American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting
Location: Pasadena, CA
Start Date: January 20, 1975
End Date: January 22, 1975
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
75A20261
Funding Number(s)
CONTRACT_GRANT: NAS2-7729
CONTRACT_GRANT: NAS1-12185
Distribution Limits
Public
Copyright
Other

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