Rakhman Gul

Date of Award

3-15-1991

Document Type

Thesis

Degree Name

Master of Science in Aeronautical Engineering

Department

Department of Aeronautics and Astronautics

First Advisor

William C. Elrod, PhD

Abstract

During this study a simple model of a flat plate was chosen to determine heat flux from a high speed flow behind a shock wave into the film cooled flat plate. An electrical analog was used to convert the output of the heat flux gages into heat flux. Free stream turbulence within the flow behind the shock wave and that generated by a turbulence generator was determined and its effects on the heat transfer data were then studied for comparison with previous experimental work. The thin-film heat flux gages were calibrated and their calibration constants were then used to determine the true heat flux into the flat plate. Film cooling flows were studied under three different primary flow conditions. Cool air was injected into the boundary layer on the flat plate, and analyzed for its effects on the heat transfer to the flat plate.

AFIT Designator

AFIT-GAE-ENY-91M-4

DTIC Accession Number

ADA238886

Comments

The author's Vita page is omitted.

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