Masters Theses

Dale M. Pitt

Abstract

"It is generally recognized that the presence of a model support sting i s likely to affect the model's base pressure and wake characteristics. The use of a wire-supported model is usually relied upon to obtain minimum disturbance measurements in the model's wake. Investigations into the disturbances caused by different size supporting wires have been conducted with the use of a 16-degree wedge and cone. The tests were conducted in the University of Missouri-Rolla axisymmetric supersonic wind tunnel at Mach 3.15, and at a Reynolds number of 2.14 X 106 per inch. Pitot pressure traverses were made in the wake of the wedge with different diameter support wires to determine the effect on the flow. Schlieren photographs were made of the wire supported cone with various size support wires. Support wires were shown to have no effect on the pitot pressures in the viscous wake or recirculation region of the wedge. The pitot pressure in the Non viscous wake was initially reduced by the presence of the support wires, but increasing the wire size resulted in no further reduction. As the cone's support wires' diameters were increased, the width of its wake increased, and the rear stagnation point location shifted toward the base. The results were in agreement with those obtained by other investigators"-- Abstract, p. 2

Advisor(s)

Selberg, B. P.

Committee Member(s)

Howell, Ronald H. (Ronald Hunter), 1935-
Kerr, Richard H., 1907-1980

Department(s)

Mechanical and Aerospace Engineering

Degree Name

M.S. in Aerospace Engineering

Publisher

University of Missouri--Rolla

Publication Date

1975

Pagination

vi, 72 pages

Note about bibliography

Includes bibliographical references (pages 18-28)

Rights

© 1975 Dale M. Pitt, All rights reserved.

Document Type

Thesis - Open Access

File Type

text

Language

English

Thesis Number

T 4073

Print OCLC #

5984832

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