Date of Award

12-1993

Document Type

Thesis

Degree Name

Master of Science in Aeronautical Engineering

Department

Department of Aeronautics and Astronautics

First Advisor

Philip S. Beran, PhD

Abstract

A numerical analysis of the aerodynamic phenomena associated with the high-speed flight of a sharp-nosed, four-finned, high-fineness ratio missile using a block-structured, parallel computer algorithm is presented. The algorithm, PANS-3EM, utilizes a second-order-accurate, shock-capturing, Total Variation Diminishing scheme and incorporates a Baldwin-Lomax turbulence model. PANS-3EM allows for extreme flexibility in the choice of computational domain decomposition and computing machine of implementation. Developmental work consists of conceptualization and verification of the algorithm as well as parallel performance and scalability studies conducted on a variety of computing platforms. Using PANS-3EM, the aerodynamic characteristics of the missile are investigated. Drag and pitching moment coefficients are computed and compared against experimental flight data. Trends in the numerical data agree with experimental results with the exception that an unexpected reversal of the stability characteristics exhibited by the missile at speeds in excess of Mach 3.75 are not confirmed by the computer code.

AFIT Designator

AFIT-GAE-ENY-93D-4

DTIC Accession Number

ADA273776

Comments

The author's Vita page is omitted.

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