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The computation of steady 3-D separated flows over aerodynamic bodies at incidence and yawThis paper describes the implementation of a general purpose 3-D NS code and its application to simulated 3-D separated vortical flows over aerodynamic bodies. The thin-layer Reynolds-averaged NS equations are solved by an implicit approximate factorization scheme. The pencil data structure enables the code to run on very fine grids using only limited incore memories. Solutions of a low subsonic flow over an inclined ellipsoid are compared with experimental data to validate the code. Transonic flows over a yawed elliptical wing at incidence are computed and separations occurred at different yaw angles are discussed.
Document ID
19860034955
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Pulliam, T. H.
(NASA Ames Research Center Moffett Field, Stanford, CA, United States)
Pan, D.
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1986
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 86-0109
Accession Number
86A19693
Funding Number(s)
CONTRACT_GRANT: NCA2-IR-745-404
Distribution Limits
Public
Copyright
Other

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