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August 3, 2010, 11:25
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2d supersonic combustion with H2 gas
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New Member
Roshan S Lal
Join Date: Jul 2010
Posts: 5
Rep Power: 17  |
Hi friends
I'm trying to model a supersonic reacting flow with crosswise injection of hydrogen gas at mach 1 into mach 2.5 main air stream. I'm using finite rate combustion model with the fluent 6.3 solver I want to find the combustion efficieny. And in the papers its given as ηc = 1 – [ ∫αρu dA / ∑m fuel in ] ; α = mass fraction of fuel How to evaluate this formula with fluent reports. Should I find the term ∫αρu dA by surface integral and flow rate with α as the variable. Is there any other means to get efficiency of combustion Plz help me......... Roshan |
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