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An examination of injector/combustor design effects on scramjet performanceDescription of a simplified one-dimensional treatment of fuel injection for supersonic combustor performance analysis. Representative mixing efficiency variations for both parallel and cross-stream injection are obtained, and approximate means for estimating the length required for complete mixing are demonstrated. Comparisons of calculated and measured data show good agreement.
Document ID
19740057224
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Anderson, G. Y. (NASA Langley Research Center Hampton, Va., United States)
Date Acquired
August 7, 2013
Publication Date
January 1, 1974
Subject Category
Propulsion Systems
Meeting Information
Meeting: International Symposium on Air Breathing Engines
Location: Sheffield
Start Date: March 24, 1974
End Date: March 29, 1974
Accession Number
74A39974
Distribution Limits
Public
Copyright
Other

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