Investigation of air flow near a mach number of one by the Schileren Method.
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Authors
Watkins, David Wayne, Jr.
Subjects
Advisors
Keenan, J. H.
Date of Issue
1946-06
Date
June 1946
Publisher
Massachusetts Institute of Technology
Language
Abstract
The problem investigated was the manner of dissipation of shocks in air flowing through a nozzle. The shocks observed were oblique shocks. They were formed by decreasing the back pressure on the nozzle exit by means of an ejector. The mouth of the nozzle was open to laboratory air. The back pressure was increased after the shocks were formed by closing the valve between the nozzle exit and the ejector, causing dissipation of the shocks. The phenomena were observed by means of a high speed movie camera. The results indicated that the shocks formed dissipated in the throat of the nozzle. They were never observed upstream from the throat.
Type
Thesis
Description
This thesis document was issued under the authority of another institution, not NPS. At the time it was written, a copy was added to the NPS Library collection for reasons not now known. It has been included in the digital archive for its historical value to NPS. Not believed to be a CIVINS (Civilian Institutions) title.
Series/Report No
Department
Aeronautical Engineering
Organization
Massachusetts Institute of Technology
Identifiers
NPS Report Number
Sponsors
Funding
Format
Citation
Distribution Statement
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.