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Mach disk from underexpanded axisymmetric nozzle flowThe flowfield associated with the underexpanded axisymmetric nozzle freejet flow including the appearance of a Mach disk has been studied. It is shown that the location and size of the Mach disk are governed by the appearance of a triple-point shock configuration and the condition that the central core flow will reach a state of 'choking at a throat'. It is recognized that coalescence of waves requires special attention and the reflected wave, as well as the vorticity generated from these wave interactions, have to be taken accurately into account. The theoretical results obtained agreed well with the experimental data.
Document ID
19740055860
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Chang, I.-S.
Chow, W. L.
(Illinois, University Urbana, Ill., United States)
Date Acquired
August 7, 2013
Publication Date
August 1, 1974
Publication Information
Publication: AIAA Journal
Volume: 12
Subject Category
Aerodynamics
Accession Number
74A38610
Funding Number(s)
CONTRACT_GRANT: NGL-14-005-140
Distribution Limits
Public
Copyright
Other

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