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Experiments on Cruise Propulsion with a Hydrogen ScramjetMeasurement of drag have been made in a shock tunnel on a simple integrated vehicle engine combination for hypersonic cruise with hydrogen scramjet propulsion. The test flow Mach number was 6.4, and the velocity was 2.45 kms(exp -1). Zero Drag, which is the necessary condition for cruise, was achieved as the equivalence ratio approached one. It was found that an analysis using established aerodynamic concept was adequate for predicting drag in the case of no combustion. When combustion occurred results of direct connect experiments provided was qualitative guide to the measured levels of drag, and indicated that thrust nozzle combustion was taking place. An heuristic analysis is used to point to the important effect this may have on propulsive lift.
Document ID
19990101889
Acquisition Source
Headquarters
Document Type
Reprint (Version printed in journal)
Authors
Stalker, R. J.
(Queensland Univ. Brisbane, Australia)
Paull, A.
(Queensland Univ. Brisbane, Australia)
Date Acquired
August 19, 2013
Publication Date
January 1, 1998
Publication Information
Publication: The Aeronautical Journal
Volume: 102
Issue: 1011
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
Paper 2250
Funding Number(s)
CONTRACT_GRANT: NAGw-674
Distribution Limits
Public
Copyright
Other
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