Consider a ramjet engine at an altitude where temperature is 223 K. The flight Mach number is M = 4. At the entrance to the burner, the Mach number is 0.3. Combustion in the burner (whose cross-sectional area is constant) may be represented approximately as heating of a perfect gas with constant specific heat ratio. At the exit from the burner the temperature of the gas is 2462 K. Neglecting frictional effects in the burner and considering the flow to be one-dimensional throughout, estimate the Mach number of the gas leaving the burner. Determine also the stagnation pressure loss due to heating (i.e. calculate the ratio of outlet and inlet stagnation pressures).
