Author Type

Graduate Student

Date of Award

1988

Document Type

Thesis

Publication Status

Version of Record

Submission Date

October 2026

Thesis/Dissertation Advisor [Chair]

Bober, William

Abstract

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.

Extent

112 p.

Comments

College of Engineering and Computer Science|FAU Electronic Theses and Dissertations Collection|Thesis (M.S.)--Florida Atlantic University, 1988.|College of Engineering and Computer Science

Identifier

FADT14428

Format

pdf

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