NASA NTRS · 19940020298
HYPULSE combustor analysis
Abstract
The analysis of selected data from tests of unit fuel injectors in a generic scramjet combustor model is presented. The tests were conducted in the NASA HYPULSE expansion tube at conditions typical of flight at Mach 13.5 and 17. The analysis used a three-stream tube method, with finite-rate chemistry, in which the fuel, test gas, and mixing/combustive streams were treated independently but with the same static pressure. Performance of three candidate fuel injectors is examined based on deduced mixing and combustion efficiencies.
Keep this discovery
Explore connections, maps & timelines
Rizkalla, O. F.. 1993-12-01. HYPULSE combustor analysis. https://ntrs.nasa.gov/citations/19940020298
Cite the original work for its findings. Save a collection to share your selection of sources.