Date of Award

Spring 1989

Document Type

Thesis

Degree Name

Master of Science (MS)

Department

Mechanical & Aerospace Engineering

Program/Concentration

Mechanical Engineering

Committee Director

A. Sidney Roberts, Jr.

Committee Member

Griffith J. McRee

Committee Member

Gregory V. Selby

Committee Member

Debra L. Carraway

Call Number for Print

Special Collections; LD4331.E56O78

Abstract

Shock tube experiments have been performed to determine the response of a hot-film sensor, mounted flush on the side-wall of a shock tube, to unsteady flow behind a normal shock wave. The present experiments attempt to isolate the response of the anemometer due only to the change in convective heat transfer at the hot-film surface. The experiments, performed at low supersonic shock speeds in air, are described along with the data acquisition procedure. The change in convective heat transfer i s deduced from the data and the results are compared with those from transient boundary-layer theory and another set of experimental results. Finally, a transient local heat transfer coefficient is formulated for use as the forcing function in a hot-film sensor instrument model simulation.

Rights

In Copyright. URI: http://rightsstatements.org/vocab/InC/1.0/ This Item is protected by copyright and/or related rights. You are free to use this Item in any way that is permitted by the copyright and related rights legislation that applies to your use. For other uses you need to obtain permission from the rights-holder(s).

DOI

10.25777/1b46-6s51

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