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Nonequilibrium turbulence modeling effects on transonic vortical flows about delta wingsThe Johnson-King turbulence model that is a viable method for calculating two dimensional transonic separated flows was extended into three dimensions. The implementation was done for Navier Stokes flow solvers written in general curvilinear coordinates. The present approach used in turbulence modeling is based on streamwise integration of an ordinary differential equation (o.d.e.) that governs the maximum Reynolds shear stress behavior. Streamwise integration of the o.d.e. approach was found to offer great mathematical simplicity and economy for three dimensional Navier Stokes methods. Thus, the new method is quick, simple, and very cheap. The new method was first checked against the data of a well known transonic axisymmetric bump experiment, and a good agreement was obtained. Later, the new method was used to compute the flow around a low aspect ratio wing in a transonic wind tunnel. Finally it was employed to study the nonequilibrium turbulence effects on the transonic vortical flows about a 65 deg sweep round leading edge delta wing.
Document ID
19920003789
Acquisition Source
Ames Research Center
Document Type
Conference Paper
Authors
Unver Kaynak
(Turkish Aerospace Industries (Turkey) Ankara, Turkey)
Eugene Tu
(Ames Research Center Mountain View, California, United States)
Mustafa Dindar
(Turkish Aerospace Industries (Turkey) Ankara, Turkey)
Remzi Barlas
(Turkish Aerospace Industries (Turkey) Ankara, Turkey)
Date Acquired
September 6, 2013
Publication Date
July 1, 1991
Publication Information
Publication: AGARD, Vortex Flow Aerodynamics
Subject Category
Aerodynamics
Accession Number
92N13007
Funding Number(s)
PROJECT: Southern Flank Countries Program, No. T-57,
Distribution Limits
Public
Copyright
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