2d supersonic combustion with H2 gas
 

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