Date of Award

Summer 1991

Document Type

Thesis

Degree Name

Master of Science (MS)

Department

Mechanical & Aerospace Engineering

Program/Concentration

Mechanical Engineering

Committee Director

Arthur C. Taylor III

Committee Member

Gene J. W. Hou

Committee Member

Surendra N. Tiwari

Call Number for Print

Special Collections; LD4331.E56K67

Abstract

An approximation method is presented for efficiently predicting the changes which occur in a steady-state numerical solution of the Euler equations as a consequence of a small change in the geometric shape of the domain. The method is extended to develop a general procedure for calculating aerodynamic sensitivity derivatives with respect to variations of geometric shape. The techniques are implemented using an upwind cell centered finite volume formulation, and are applied to two test cases, (1) a subsonic nozzle (M = 0.85), and (2) a supersonic inlet (M = 2.0). Conventional numerical solutions are first obtained for flow through three slightly different geometric shapes, and one of these solutions is defined to be the known "baseline" solution. The approximation method is then used to generate predicted solutions from the baseline solution for the remaining two shapes, which compare very well with the conventional numerical solutions, and are computationally less expensive to obtain. With a simple extension of the approximation method, the sensitivity derivatives of the aerodynamic forces on the interior walls of the baseline nozzle / inlet are computed with respect to variations in the geometric shape parameters. The sensitivity coefficients calculated using this approach compare extremely well with those calculated using the method of "brute force" (finite differences), and are also computationally less expensive to obtain.

Rights

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DOI

10.25777/0vss-w238

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