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Numerical solution of two-dimensional incompressible flow about an airfoil

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Date Issued:
1988
Summary:
A numerical scheme for determining the two dimensional, incompressible flow field about an airfoil is described. The scheme combines two methods: the Neumann (panel) method to determine the potential flow and a hybrid numerical method to determine the boundary layer flow. In the panel method, the fundamental theorems of potential theory are employed to derive the pressure and velocity fields around and along the airfoil. The velocity field obtained in the panel method is used in the hybrid method to determine the boundary layer thickness along the surface of the airfoil. The hybrid numerical method is an implicit finite difference numerical scheme which combines central and upwind differencing for the convective terms. The boundary layer thickness obtained is introduced back into the panel method to determine new pressure and velocity fields, thus imposing the effects of laminar, viscous flow on the solution. Lift coefficients for various angles of attack are derived and compared with experimental data presented in appropriate NACA technical reports. Reasonable agreement was obtained.
Title: Numerical solution of two-dimensional incompressible flow about an airfoil.
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Name(s): Barnes, Robert Stuart.
Florida Atlantic University, Degree grantor
Bober, William, Thesis advisor
Type of Resource: text
Genre: Electronic Thesis Or Dissertation
Issuance: monographic
Date Issued: 1988
Publisher: Florida Atlantic University
Place of Publication: Boca Raton, Fla.
Physical Form: application/pdf
Extent: 112 p.
Language(s): English
Summary: A numerical scheme for determining the two dimensional, incompressible flow field about an airfoil is described. The scheme combines two methods: the Neumann (panel) method to determine the potential flow and a hybrid numerical method to determine the boundary layer flow. In the panel method, the fundamental theorems of potential theory are employed to derive the pressure and velocity fields around and along the airfoil. The velocity field obtained in the panel method is used in the hybrid method to determine the boundary layer thickness along the surface of the airfoil. The hybrid numerical method is an implicit finite difference numerical scheme which combines central and upwind differencing for the convective terms. The boundary layer thickness obtained is introduced back into the panel method to determine new pressure and velocity fields, thus imposing the effects of laminar, viscous flow on the solution. Lift coefficients for various angles of attack are derived and compared with experimental data presented in appropriate NACA technical reports. Reasonable agreement was obtained.
Identifier: 14428 (digitool), FADT14428 (IID), fau:11228 (fedora)
Collection: FAU Electronic Theses and Dissertations Collection
Note(s): College of Engineering and Computer Science
Thesis (M.S.)--Florida Atlantic University, 1988.
Subject(s): Aerofoils--Aerodynamics
Held by: Florida Atlantic University Libraries
Persistent Link to This Record: http://purl.flvc.org/fcla/dt/14428
Sublocation: Digital Library
Use and Reproduction: Copyright © is held by the author, with permission granted to Florida Atlantic University to digitize, archive and distribute this item for non-profit research and educational purposes. Any reuse of this item in excess of fair use or other copyright exemptions requires permission of the copyright holder.
Use and Reproduction: http://rightsstatements.org/vocab/InC/1.0/
Host Institution: FAU
Is Part of Series: Florida Atlantic University Digital Library Collections.