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A numerical method for computing unsteady 2-D boundary layer flowsA numerical method for computing unsteady two-dimensional boundary layers in incompressible laminar and turbulent flows is described and applied to a single airfoil changing its incidence angle in time. The solution procedure adopts a first order panel method with a simple wake model to solve for the inviscid part of the flow, and an implicit finite difference method for the viscous part of the flow. Both procedures integrate in time in a step-by-step fashion, in the course of which each step involves the solution of the elliptic Laplace equation and the solution of the parabolic boundary layer equations. The Reynolds shear stress term of the boundary layer equations is modeled by an algebraic eddy viscosity closure. The location of transition is predicted by an empirical data correlation originating from Michel. Since transition and turbulence modeling are key factors in the prediction of viscous flows, their accuracy will be of dominant influence to the overall results.
Document ID
19890003464
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Krainer, Andreas
(Naval Postgraduate School Monterey, CA, United States)
Date Acquired
September 5, 2013
Publication Date
December 1, 1988
Publication Information
Publisher: NASA
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
NAS 1.26:4198
NASA-CR-4198
E-4394
Accession Number
89N12835
Funding Number(s)
PROJECT: RTOP 582-01-11
CONTRACT_GRANT: NASA ORDER C-80017-F
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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