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Transonic Flow Field Analysis for Wing-Fuselage ConfigurationsA computational method for simulating the aerodynamics of wing-fuselage configurations at transonic speeds is developed. The finite difference scheme is characterized by a multiple embedded mesh system coupled with a modified or extended small disturbance flow equation. This approach permits a high degree of computational resolution in addition to coordinate system flexibility for treating complex realistic aircraft shapes. To augment the analysis method and permit applications to a wide range of practical engineering design problems, an arbitrary fuselage geometry modeling system is incorporated as well as methodology for computing wing viscous effects. Configuration drag is broken down into its friction, wave, and lift induced components. Typical computed results for isolated bodies, isolated wings, and wing-body combinations are presented. The results are correlated with experimental data. A computer code which employs this methodology is described.
Document ID
19800016802
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Boppe, C. W. (Grumman Aerospace Corp. Bethpage, NY, United States)
Date Acquired
September 4, 2013
Publication Date
May 1, 1980
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-3243
Accession Number
80N25295
Funding Number(s)
CONTRACT_GRANT: NAS1-14732
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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