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Navier-Stokes prediction of a delta wing in roll with vortex breakdownThe three-dimensional, Reynolds-averaged, Navier-Stokes (RANS) equations are used to numerically simulate vortical flow about a 65 degree sweep delta wing. Subsonic turbulent flow computations are presented for this delta wing at 30 degrees angle of attack and static roll angles up to 42 degrees. This work is part of an on going effort to validate the RANS approach for predicting high-incidence vortical flows, with the eventual application to wing rock. The flow is unsteady and includes spiral-type vortex breakdown. The breakdown positions, mean surface pressures, rolling moments, normal forces, and streamwise center-of-pressure locations compare reasonably well with experiment. In some cases, the primary vortex suction peaks are significantly underpredicted due to grid coarseness. Nevertheless, the computations are able to predict the same nonlinear variation of rolling moment with roll angle that appeared in the experiment. This nonlinearity includes regions of local static roll instability, which is attributed to vortex breakdown.
Document ID
19930063270
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Chaderjian, Neal M.
(NASA Ames Research Center Moffett Field, CA, United States)
Schiff, Lewis B.
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Publication Information
Publication: In: AIAA Applied Aerodynamics Conference, 11th, Monterey, CA, Aug. 9-11, 1993, Technical Papers. Pt. 2 (A93-47201 19-02)
Publisher: American Institute of Aeronautics and Astronautics
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 93-3495
Accession Number
93A47267
Distribution Limits
Public
Copyright
Other

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