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Scramjet nozzle design and analysis as applied to a highly integrated hypersonic research airplaneThe configuration and performance of the propulsion system for the hypersonic research vehicle are discussed. A study of the interactions between propulsion and aerodynamics of the highly integrated vehicle was conducted. The hypersonic research vehicle is configured to test the technology of structural and thermal protection systems concepts and the operation of the propulsion system under true flight conditions for most of the hypersonic flight regime. The subjects considered are: (1) research vehicle and scramjet engine configurations to determine fundamental engine sizing constraints, (2) analytical methods for computing airframe and propulsion system components, and (3) characteristics of a candidate nozzle to investigate vehicle stability and acceleration performance.
Document ID
19750005793
Document Type
Technical Memorandum (TM)
Authors
Small, W. J.
(NASA Langley Research Center Hampton, VA, United States)
Weidner, J. P.
(NASA Langley Research Center Hampton, VA, United States)
Johnston, P. J.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
November 1, 1974
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-TM-X-71972
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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