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A model for 3-D sonic/supersonic transverse fuel injection into a supersonic air streamA model for sonic/supersonic transverse fuel injection into a supersonic airstream is proposed. The model replaces the hydrogen jet up to the Mach disk plane and the elliptic parts of the air flow field around the jet by an equivalent body. The main features of the model were validated on the basis of experimental data.
Document ID
19890038005
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Bussing, Thomas R. A. (Boeing Advanced Systems Co. Seattle, WA, United States)
Lidstone, Gary L. (Boeing Advanced Systems Seattle, WA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1989
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
AIAA PAPER 89-0460
Report Number: AIAA PAPER 89-0460
Accession Number
89A25376
Funding Number(s)
CONTRACT_GRANT: NAS1-18560
Distribution Limits
Public
Copyright
Other

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