In a supersonic combustion concept air enters the combustor with Mach number 6, static pressure of 1 atm, and temperature 1500 K. Hydrogen (in the stoichiometrically correct proportion) enters the combustor with the same velocity, pressure and temperature as the air and mixes with the air without frictional loss. Combustion proceeds to completion over a distance of 1 m with the fuel-burned fraction proportional to distance x from the inlet. During combustion the mixture accelerates in such a way as to keep the static temperature constant
a.Determine the variation of mixture velocity and molecular weight with distance x.
b.Determine the exit Mach number.
c.Show how to determine the exit static pressure and the ratio of outlet to inlet area.
Use the same specific heat and heat of formation values as in Problem 11 and take γ = 1.35 for air.
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