Date of Award

12-1992

Document Type

Thesis

Degree Name

Master of Science

Department

Department of Aeronautics and Astronautics

First Advisor

Gerald A. Hasen, PhD

Abstract

This study investigated the effects of the interaction between the viscous boundary layer and the shock wave produced by a Mach 10 inviscid optimized waverider. An implicit, Roe flux-splitting algorithm, developed by WL/FIMM, was used to solve the flow field. A validation for the inviscid version of the CFD algorithm was accomplished by comparing the numerical -data produced by the CFD code to the analytic results derived by Rasmussen, and by comparison to results of the explicit version of the same Roe flux-splitting code. The computational results compared favorably. The inviscid case studied using the implicit code produced results identical, for all practical purposes, to those of the explicit code, though approximately twice as quickly. The results of the viscous flow case matched well with the results predicted by theory. The lift to drag ratio calculated, 5.74, is comparable to the results of other researchers.

AFIT Designator

AFIT-GAE-ENY-92D-23

DTIC Accession Number

ADA259019

Comments

The author's Vita page is omitted.

Download

Share

COinS