On 3D boundary layer computations on swept wings

Subramanian, NR and James, M (1987) On 3D boundary layer computations on swept wings. Technical Report. National Aeronautical Laboratory, Bangalore, India.

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Abstract

A three-dimensional turbulent boundary layer code based on an integral method developed by Cousteix and Aupoix has been made operational on the NAL computer. The turbulent modeling is based on an improved mixing length hypothesis and similarity solutions. This code is developed for a general coordinate system for flows up to Mach number 4 on an adiabatic wall. Two test cases (NLR supercritical wing and ONERA-M6 wing) have been tested using this program. Results for the NLR wing have been compared with the available computer results. (Author)

Item Type: Proj.Doc/Technical Report (Technical Report)
Uncontrolled Keywords: Supercritical wings;Swept wings;Turbulent boundary layer;Mach number;Wind tunnel tests
Subjects: AERONAUTICS > Aeronautics (General)
Division/Department: Computational and Theoretical Fluid Dynamics Division, Other
Depositing User: M/S ICAST NAL
Date Deposited: 07 Nov 2006
Last Modified: 24 May 2010 09:52
URI: http://nal-ir.nal.res.in/id/eprint/3128

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