Degree Type

Dissertation

Date of Award

1993

Degree Name

Doctor of Philosophy

Department

Aerospace Engineering

First Advisor

Alric P. Rothmayer

Abstract

The details of an interacting boundary layer algorithm capable of calculating large scale laminar separation past airfoils at low speeds is given. Rationale behind various convergence acceleration methods is given. It is shown that linear based acceleration methods are limited to 50% savings in convergence rate. A nonlinear extrapolation method is proposed and tested on two simple model problems. Savings exceed the 50% limitation of the previous methods. Boundary layer results for laminar flow past symmetric airfoils at zero incidence are presented as a test of the methods. Leading edge marginal separation results at finite Reynolds numbers are presented. Richardson extrapolation of successive calculations is used to improve accuracy. Results for a zero thickness uncambered plate at angle of attack are presented.

DOI

https://doi.org/10.31274/rtd-180813-9595

Publisher

Digital Repository @ Iowa State University, http://lib.dr.iastate.edu/

Copyright Owner

Daniel Wayne Black

Language

en

Proquest ID

AAI9334962

File Format

application/pdf

File Size

183 pages

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