Dual-mode combustion of hydrogen in a mach 5, continuous-flow facility

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dc.contributor.author Goyne, C.
dc.contributor.author McDaniel, J.
dc.contributor.author Quagliaroli, T.
dc.contributor.author Krauss, R.
dc.contributor.author Day, Steven
dc.date.accessioned 2009-03-17T16:22:57Z
dc.date.available 2009-03-17T16:22:57Z
dc.date.issued 2001-11
dc.identifier.uri http://hdl.handle.net/1850/8588
dc.description Journal of propulsion and power abstract. Please see http://www.aiaa.org for more information. en_US
dc.description.abstract Results of an experimental and numerical study of a dual-mode scramjet combustor are reported. The experiment consisted of a direct-connect test of a Mach 2 hydrogen-air combustor with a single unswept-ramp fuel injector. The flow stagnation enthalpy simulated a flight Mach number of S. Measurements were obtained using conventional wall instrumentation and a particle-imaging laser diagnostic technique. The particle imaging was enabled through the development of a new apparatus for seeding fine silicon dioxide particles into the combustor fuel stream. Numerical simulations of the combustor were performed using the GASP code. The modeling, and much of the experimental work, focused on the supersonic combustion mode. Reasonable agreement was observed between experimental and numerical wall pressure distributions. However, the numerical model was unable to predict accurately the effects of combustion on the fuel plume size, penetration, shape, and axial growth. en_US
dc.language.iso en_US en_US
dc.publisher Journal of propulsion and power en_US
dc.relation.ispartofseries Vol. 17 en_US
dc.relation.ispartofseries No. 6 en_US
dc.subject Hydrogen-air combustor en_US
dc.subject Particle-imaging en_US
dc.subject Schmidt number en_US
dc.subject Silicon dioxide en_US
dc.title Dual-mode combustion of hydrogen in a mach 5, continuous-flow facility en_US
dc.type Article en_US

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