NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Subsonic panel method for the efficient analysis of multiple geometry perturbationsAn accurate and efficient method was developed for the aerodynamic analysis of a series of arbitrary small geometry perturbations to a given baseline configuration. The method is appropriate for wing-fuselage configurations in incompressible potential flow. Mathematical formulations are presented for three computer programs that are employed. The first program is a conventional surface panel method for calculating the baseline singularity distribution. The second program calculates a partial derivative matrix. Each element of the matrix is the rate of change of singularity strength at one point with respect to a surface coordinate of a different point. For each baseline configuration, the calculated quantities from the first two programs establish an input file for the third. The third program calculates the surface pressure distribution and forces and moments for a series of geometry perturbations.
Document ID
19820011306
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Bristow, D. R. (McDonnell-Douglas Corp. Saint Louis, MO, United States)
Hawk, J. D. (McDonnell-Douglas Corp. Saint Louis, MO, United States)
Date Acquired
September 4, 2013
Publication Date
March 1, 1982
Publication Information
Publisher: NASA
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-3528
Accession Number
82N19180
Funding Number(s)
CONTRACT_GRANT: NAS1-16156
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available