A combustion chamber consists of tubular combustors of 15 cm diameter. Compressed air enters the tubes at 550 K, 480 kPa, and 80 m/s. Fuel with a heating value of 42,000 kJ/kg is injected into the air and is burned with an air-fuel ratio of 40. Approximating the combustion as a heat transfer process to air, determine the temperature, pressure, velocity, and Mach number at the exit of the combustion chamber. Assume the flow is frictionless.