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Hydrogen scramjet with side wall injectionPreliminary results are presented from an experimental evaluation of a hydrogen-burning wall-injection scramjet engine, performed in the free-piston shock tunnel at the Australian National University. The advantages of scramjet propulsion for high-Mach-number high-altitude flight are reviewed, and the need for an alternative to injection struts is indicated. Pressure profiles and heat-transfer measurements for constant-area and diverging ducts are presented graphically and characterized in detail. The ability of the injected flow to shield the chamber wall from the heat of the freestream flow is demonstrated. The extrapolation of the shock-tunnel results to flight conditions, however, is made difficult by the fact that a significant amount of fuel passes through a quenched zone without burning, seriously degrading overall performance.
Document ID
19880028300
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Morgan, R. G.
Paull, A.
Morris, N.
Stalker, R. J.
Date Acquired
August 13, 2013
Publication Date
January 1, 1986
Subject Category
Aircraft Propulsion And Power
Meeting Information
Meeting: National Space Engineering Symposium
Location: Sydney
Country: Australia
Start Date: March 25, 1986
End Date: March 27, 1986
Accession Number
88A15527
Funding Number(s)
CONTRACT_GRANT: NAGW-674
Distribution Limits
Public
Copyright
Other

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