Actions for Scramjet sidewall burning : Preliminary shock tunnel results

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Scramjet sidewall burning : Preliminary shock tunnel results

Author
Stalker, R. J.
Published
JAN 1, 1985.
Physical Description
1 electronic document
Additional Creators
Morgan, R. G., Morris, N., and Paull, A.
Online Version

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Unclassified, Unlimited, Publicly available.
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Summary
Experiments 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.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19860005867.
Accession ID: 86N15337.
REPT-12/85.
NAS 1.26:176420.
NASA-CR-176420.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15703520