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A linear shock cell model for jets of arbitrary exit geometryThe shock cell structures of single supersonic non-ideally expanded jets with arbitrary exit geometry are studied. Both vortex sheets and realistic mean profiles are considered for the jet shear layer. The boundary element method is used to predict the shock spacing and screech tones in a vortex sheet model of a single jet. This formulation enables the calculations to be performed only on the vortex sheet. This permits the efficient and convenient study of complicated jet geometries. Results are given for circular, elliptic and rectangular jets and the results are compared with analysis and experiment. The agreement between the predictions and measurements is very good but depends on the assumptions made to predict the geometry of the fully expanded jet. A finite diffference technique is used to examine the effect of finite mixing layer thickness for a single jet. The finite thickness of the mixing layer is found to decrease the shock spacing by approximately 20 percent over the length of the jet potential core.
Document ID
19890062781
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Morris, P. J.
(Pennsylvania State Univ. University Park, PA, United States)
Bhat, T. R. S.
(Pennsylvania State Univ. University Park, PA, United States)
Chen, G.
(Pennsylvania State University University Park, United States)
Date Acquired
August 14, 2013
Publication Date
July 22, 1989
Publication Information
Publication: Journal of Sound and Vibration
Volume: 132
ISSN: 0022-460X
Subject Category
Fluid Mechanics And Heat Transfer
Accession Number
89A50152
Funding Number(s)
CONTRACT_GRANT: AF-AFOSR-87-0334
CONTRACT_GRANT: NAG1-657
Distribution Limits
Public
Copyright
Other

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