Degree Type

Dissertation

Date of Award

1987

Degree Name

Doctor of Philosophy

Department

Aerospace Engineering

Abstract

A new computer code for the solution of the three-dimensional parabolized Navier-Stokes (PNS) equations has been developed. The code employs a state-of-the-art upwind algorithm to capture strong shock waves. The algorithm developed in this work is implicit, uses finite-volumes, and is second-order accurate in the crossflow directions. The new code is validated through application to several laminar supersonic and hypersonic flows. In two dimensions, calculations were performed for supersonic laminar flow past a flat plate, hypersonic laminar flow past a 15(DEGREES) compression corner, and hypersonic laminar flow into a converging inlet. Results obtained using the present algorithm are in excellent agreement with experimental data as well as with previous numerical calculations. The method was validated for three-dimensional flow by computing hypersonic flows past two simple body shapes: a circular cone of 10(DEGREES) half-angle and a generic all-body hypersonic vehicle. Cone flow solutions were computed at angles of attack of 12(DEGREES), 20(DEGREES), and 24(DEGREES) and results are in agreement with experimental data. Results are also presented for the flow past the all-body vehicle at angles of incidence of 0(DEGREES) and 10(DEGREES).

DOI

https://doi.org/10.31274/rtd-180813-8623

Publisher

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

Copyright Owner

Scott Leroy Lawrence

Language

en

Proquest ID

AAI8716785

File Format

application/pdf

File Size

98 pages

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