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Scramjet sidewall burning: Preliminary shock tunnel resultsExperiments performed with a two dimensional model scramjet with particular emphasis on the effect of fuel injection from a wall are reported. Air low with a nominal Mach number of 3.5 and varied enthalpies was produced. It was found that neither hydrogen injection angle nor combustor divergence angle had any appreciable effect on thrust values while increased combustor length appeared to increase thrust levels. Specific impulse was observed to peak when hydrogen was injected at an equivalence ratio of about 2. Lowering the Mach number of the injected hydrogen at low equivalence ratios, less than 4, appeared to benefit specific impulse while hydrogen Mach number had little effect at higher equivalence ratios. When a 1:1 mixture by volume of nitrogen and oxygen is used instead of air as a test gas, it is found that hydrogen combustion is enhanced but only at high enthalpies.
Document ID
19860005867
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Morgan, R. G. (Queensland Univ. Brisbane, Australia)
Paull, A. (Queensland Univ. Brisbane, Australia)
Morris, N. (Queensland Univ. Brisbane, Australia)
Stalker, R. J. (Queensland Univ. Brisbane, Australia)
Date Acquired
September 5, 2013
Publication Date
January 1, 1985
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
REPT-12/85
NASA-CR-176420
NAS 1.26:176420
Accession Number
86N15337
Funding Number(s)
CONTRACT_GRANT: NAGW-674
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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