NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Mach 2 combustion characteristics of hydrogen/hydrocarbon fuel mixturesThe combustion of H2/CH4 and H2/C2H4 mixtures containing 10 to 70 vol pct hydrocarbon at combustor inlet Mach number 2 and temperatures 2000 to 4000 R is investigated experimentally, applying direct-connect test hardware and techniques similar to those described by Diskin and Northam (1987) in the facilities of the NASA Langley Hypersonic Propulsion Branch. The experimental setup, procedures, and data-reduction methods are described; and the results are presented in extensive tables and graphs and characterized in detail. Fuel type and mixture are found to have little effect on the wall heating rate measured near the combustor exit, but H2/C2H4 is shown to burn much more efficiently than H2/CH4, with no pilot-off blowout equivalence ratios greater than 0.5. It is suggested that H2/hydrocarbon mixtures are feasible fuels (at least in terms of combustion efficiency) for scramjet SSTO vehicles operating at freestream Mach numbers above 4.
Document ID
19880016184
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Diskin, Glenn S.
(NASA Langley Research Center Hampton, VA, United States)
Jachimowski, C. J.
(NASA Langley Research Center Hampton, VA, United States)
Northam, G. Burton
(NASA Langley Research Center Hampton, VA, United States)
Bell, Randy A.
(George Washington Univ. Hampton, Va., United States)
Date Acquired
August 13, 2013
Publication Date
October 1, 1987
Publication Information
Publication: Johns Hopkins Univ., The 24th JANNAF Combustion Meeting, Volume 2
Subject Category
Inorganic And Physical Chemistry
Accession Number
88N25568
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Available Downloads

There are no available downloads for this record.
No Preview Available