Date of Award:

12-2024

Document Type:

Thesis

Degree Name:

Master of Science (MS)

Department:

Mechanical and Aerospace Engineering

Committee Chair(s)

Douglas F. Hunsaker

Committee

Douglas F. Hunsaker

Committee

Som Dutta

Committee

Thomas H. Fronk

Committee

Jeffrey D. Taylor

Abstract

This thesis presents an improved vortex wake model for unstructured, supersonic panel methods. Panel methods are numerical methods that utilize inviscid flow assumptions and other simplifications to allow efficient computation of pressure distributions, velocity fields, and aerodynamic forces. They are commonly used for preliminary design, automatic design codes, and automatic optimization routines. Most existing supersonic panel methods do not include automatic wake generation and relaxation. This prevents the accurate analysis of many geometries, including those with conventional horizontal stabilizers or canards. This thesis first outlines the derivation of a relaxable generalized supersonic vortex filament equation. Next, it explores other necessary developments required to implement this equation. The equation is then shown to match existing canonical cases within expected numerical precision. Finally, studies using wake relaxation are presented. These comparisons show that the presented model converges to a single solution and allows for the computation of complex geometries, providing the assumptions are representative of the cases analyzed.

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