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Performance of an inlet for an integrated scramjet conceptReview of the results of an experimental investigation of the performance of an inlet for an integrated scramjet engine concept at Mach 6. Following a description of the inlet design and test model, the Mach 6 experimental results obtained are presented in terms of integrated performance parameters.
Document ID
19740061674
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Trexler, C. A. (NASA Langley Research Center Hypersonic Vehicles Div., Hampton, Va., United States)
Date Acquired
August 7, 2013
Publication Date
September 1, 1974
Publication Information
Publication: Journal of Aircraft
Volume: 11
Subject Category
Aircraft
Accession Number
74A44424
Distribution Limits
Public
Copyright
Other

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