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Experiments on hypersonic ramjet propulsion cycles using a ram acceleratorWork on hypersonic propulsion research using a ram accelerator is presented. Several different ram accelerator propulsive cycles have been experimentally demonstrated over the Mach number range of 3 to 8.5. The subsonic, thermally choked combustion mode has accelerated projectiles to near the Chapman-Jouguet (C-J) detonation velocity within many different propellant mixtures. In the transdetonative velocity regime (85 to 115 percent of C-J speed), projectiles have established a propulsive cycle which allows them to transition smoothly from subdetonative to superdetonative velocities. Luminosity data indicate that the combustion process moves forward onto the projectile body as it approaches the C-J speed. In the superdetonative velocity range, the projectiles accelerate while always traveling faster than the C-J velocity. Ram accelerator projectiles operating continuously through these velocity regimes generate distinctive hypersonic phenomena which can be studied very effectively in the laboratory. These results would be very useful for validating sophisticated CFD computer codes and in collecting engineering data for potential airbreathing hypersonic propulsive systems.
Document ID
19910059641
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Chew, G.
(Washington Univ. Seattle, WA, United States)
Knowlen, C.
(Washington Univ. Seattle, WA, United States)
Burnham, E. A.
(Washington Univ. Seattle, WA, United States)
Hertzberg, A.
(Washington Univ. Seattle, WA, United States)
Bruckner, A. P.
(Washington, University Seattle, United States)
Date Acquired
August 15, 2013
Publication Date
June 1, 1991
Subject Category
Research And Support Facilities (Air)
Report/Patent Number
AIAA PAPER 91-2489
Accession Number
91A44264
Funding Number(s)
CONTRACT_GRANT: F08635-89-C-0196
CONTRACT_GRANT: NAG1-327
CONTRACT_GRANT: NAG1-1061
Distribution Limits
Public
Copyright
Other

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