Date of Award

12-1992

Document Type

Thesis

Degree Name

Master of Science in Aeronautical Engineering

Department

Department of Aeronautics and Astronautics

First Advisor

John H. Doty, PhD

Abstract

This study compared the results of two computer programs, a flux- difference-splitting (FDS) Godunov-based scheme and the SCPAMjet Hypersonic Nozzle (SCHNOZ) paraobolized Navier-Stoke's code using MacCormack's method, applied to a hypersonic nozzle flowfield. Two different nozzle geometries were investigated at three Mach numbers along a typical hypersonic flight trajectory. A direct compariosn between the SCHNOZ and FDS programs was made by numerically solving the steady Euler equations using a frozen flow assumption in the nozzle. The frozen flow SCHNOZ code is currently 6 to 10 times more efficient in terms of computational time than the FDS frozen flow code. The SCHNOZ and FDS codes demonstrated comparable accuracy in modeling the flow physics. The implementation of the viscous terms in the SCHNOZ code proved to be ineffectual in modeling the viscous effects in the flowfield. The finite rate chemistry effects were important for the nozzle inlet conditions considered.

AFIT Designator

AFIT-GAE-ENY-92D-27

DTIC Accession Number

ADA259146

Comments

The author's Vita page is omitted.

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