Date of Award

Summer 1988

Document Type

Thesis

Degree Name

Master of Science (MS)

Department

Mechanical & Aerospace Engineering

Program/Concentration

Mechanical Engineering

Committee Director

Ernst von Lavante

Committee Member

Robert L. Ash

Committee Member

Osama S. Kandil

Call Number for Print

Special Collections; LD4331.E56C36

Abstract

A numerical method for solving three-dimensional transonic flows using the isenthalpic formulation of the Euler equations is developed. The method uses van Leer's flux vector splitting to solve the implicit formulation of the governing equations, which are applied to a cell centered finite-volume scheme. A three factor spatial approximate factorization is implemented in solving the implicit part of the governing equations. Time marching to a steady state solution requires short computational times due to the relative efficiency of the basic method. Computational times are further reduced by the implementation of the multigrid acceleration technique, which provided converged solutions in approximately 275 multigrid fixed V-cycles for the test case of an ONERA M6 wing at M = 0.84 and angle of attack n = 3.06o. Results for several basic corner flow cases are also shown, where the inlet Mach numbers are Minlet = 2.17, 3.0, 3.17 and the compression ramps were at angles α = 12.2o, 9.5o and 12.2', respectively. In addition, computational results for both the ONERA M6 wing at M = 0.699, α = 3.06o and a case for a NACA 0012 wing with a semispan of 0.75 at M = 0.80 and α = 3.0o, are shown. The results of the present scheme are in good agreement with other numerical results and experimental data; therefore choosing the isenthalpic Euler equations as the governing equations of motion for these particular types of flow configurations proved to be valid.

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DOI

10.25777/07yt-0678

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