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A source flow characteristic technique for the analysis of scramjet exhaust flow fieldThe factors which influence the design and selection of a nozzle for a hypersonic scramjet are described. A two dimensional second-order characteristic procedure capable of analyzing the aerodynamic performance of typical nozzle configurations is presented. Equations of motion governing the two dimensional, axisymmetric, or axially expanding inviscid flow of a gas mixture, with frozen chemistry, are provided. Diagrams of the flow conditions for various configurations are included.
Document ID
19740014812
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Delguidice, P. (Advanced Technology Labs., Inc. Westbury, NY, United States)
Dash, S. (Advanced Technology Labs., Inc. Westbury, NY, United States)
Kalben, P. (Advanced Technology Labs., Inc. Westbury, NY, United States)
Date Acquired
September 3, 2013
Publication Date
March 1, 1974
Subject Category
Fluid Mechanics
Report/Patent Number
NASA-CR-132437
ATL-TR-186
Report Number: NASA-CR-132437
Report Number: ATL-TR-186
Accession Number
74N22925
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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