Dual-Mode Combustion of Hydrogen in a Mach 5, Continuous-Flow Facility

Goyne, C. P.; McDaniel, J. C.; Quagliaroli, T. M.; Krauss, R. H.; Day, S. W.; Reubush, D. E.; McClinton, C. R.

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 5. 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.

Document ID

20030007791

Acquisition Source

Langley Research Center

Document Type

Reprint (Version printed in journal)

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Date Acquired

September 7, 2013

Publication Date

November 1, 2001

Publication Information

Publication: Journal of Propulsion and Power

Volume: 17

Issue: 6

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Public

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