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ENCIT 2018
Brazilian Congress of Thermal Sciences and Engineering
DESIGN AND ANALYSIS OF A SCRAMJET INLET AND COMBUSTION CHAMBER FOR HEAT ADDITION RATE INVESTIGAT
Submission Author:
Felipe Jean da Costa , SP , Brazil
Co-Authors:
Felipe Jean da Costa, David Romanelli Pinto, Gustavo Jean da Costa, Israel Rêgo, Antonio Carlos de Oliveira, Tiago Rolim, Paulo Toro
Presenter: Felipe Jean da Costa
doi://10.26678/ABCM.ENCIT2018.CIT18-0192
Abstract
This work shows preliminary results of the design and analysis of a scramjet inlet and combustor for heat addition rate studies. The inlet was modeled using oblique shockwave equations for a perfect gas and the combustor was assumed to be in chemical equilibrium, considering 10 species. Inviscid flow was assumed. The fuel was hydrogen. The scramjet design Mach number was 7.0 at an altitude of 30 km, with a design fuel equivalence ratio of 0.15. The analysis focuses on how the heat addition rate influences combustor exit temperature, Mach number and geometry. It was found that, independently of the energy added when the flow approaches Mach 1.0, the combustion exit properties values get closer.
Keywords
Scramjet, hypersonics, Propulsion, supersonic combustion
