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Aerodynamic analysis of three advanced configurations using the TranAir full-potential codeComputational results are presented for three advanced configurations: the F-16A with wing tip missiles and under wing fuel tanks, the Oblique Wing Research Aircraft, and an Advanced Turboprop research model. These results were generated by the latest version of the TranAir full potential code, which solves for transonic flow over complex configurations. TranAir embeds a surface paneled geometry definition in a uniform rectangular flow field grid, thus avoiding the use of surface conforming grids, and decoupling the grid generation process from the definition of the configuration. The new version of the code locally refines the uniform grid near the surface of the geometry, based on local panel size and/or user input. This method distributes the flow field grid points much more efficiently than the previous version of the code, which solved for a grid that was uniform everywhere in the flow field. TranAir results are presented for the three configurations and are compared with wind tunnel data.
Document ID
19890011573
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Madson, M. D. (NASA Ames Research Center Moffett Field, CA, United States)
Carmichael, R. L. (NASA Ames Research Center Moffett Field, CA, United States)
Mendoza, J. P. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 5, 2013
Publication Date
March 1, 1989
Publication Information
Publication: NASA, Langley Research Center, Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 2
Subject Category
Aerodynamics
Accession Number
89N20944
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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