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Symmetry plane model for turbulent flows with vortex generatorsAn approximate procedure is proposed for predicting the performance of counterrotating vortex-generator installations in incompressible flow. An inviscid calculation that includes the motion of the vortices is used to obtain crossflow velocities at the boundary-layer edge as a function of initial position, spacing, and strength of the vortices, and local values of the spanwise gradient are then folded into an integral turbulent-boundary layer procedure applied in the plane of symmetry. Special attention is paid to the consistency of the approximations and equations used. The two-dimensional aerodynamics of vortex generator installations on a NACA 0016 airfoil at angle-of-attack are estimated in this manner, and the results compared with experiments carried out with a 30-cm chord wing mounted in a 2.4 x 3.6-m cross-section wind tunnel and tested at chord Reynolds numbers of 0.7 and 1.4 x 10 to the 6th. Agreement in the separation location is found for these complex flows for a range of conditions.
Document ID
19910036975
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Arnaud, Gilles L.
(Washington Univ. Seattle, WA, United States)
Russell, David A.
(Washington, University Seattle, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1991
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 91-0723
Accession Number
91A21598
Funding Number(s)
CONTRACT_GRANT: NAG2-283
Distribution Limits
Public
Copyright
Other

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