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Dual-Mode CombustionThe Department of Mechanical and Aerospace Engineering at the University of Virginia has conducted an investigation of the mixing and combustion processes in a hydrogen fueled dual-mode scramjet combustor. The experiment essentially consisted of the "direct connect" continuous operation of a Mach 2 rectangular combustor with a single unswept ramp fuel injector. The stagnation enthalpy of the test flow simulated a flight Mach number of 5. Measurements were obtained using conventional wall instrumentation and laser based diagnostics. These diagnostics included, pressure and wall temperature measurements, Fuel Plume Imaging (FPI) and Particle Image Velocimetry (PIV). A schematic of the combustor configuration and a summary of the measurements obtained are presented. The experimental work at UVa was parallel by Computational Fluid Dynamics (CFD) work at NASA Langley. The numerical and experiment results are compared in this document.
Document ID
20030007792
Acquisition Source
Langley Research Center
Document Type
Contractor or Grantee Report
Authors
Goyne, Christopher P.
(Virginia Univ. Charlottesville, VA United States)
McDaniel, James C.
(Virginia Univ. Charlottesville, VA United States)
Date Acquired
September 7, 2013
Publication Date
October 1, 2002
Subject Category
Inorganic, Organic And Physical Chemistry
Funding Number(s)
CONTRACT_GRANT: NAG1-2131
Distribution Limits
Public
Copyright
Public Use Permitted.
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