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QUESTION 13 A turbine nozzle vane at high speed exhibits a normal shock. The flow is modelled as analogous to that through a convergent-divergent de Laval nozzle with a normal shock at the nozzle exit. Just upstream of the shock, the exit Mach number Me = 1.09, the absolute static pressure pe = 280 kPa, the static temperature Te = 586 K, the ratio of specific heats of the combustion products k = 1.35, and the constant pressure specific heat capacity Cp = 1027 J kg 1K-1 Assuming the combustion products are constant property ideal gasses, determine the density of the combustion products Pb after the shock. State your answer in kg m to two decimal places and enter the numerical value only. Partial credit is awarded for a reasonable approximation to the correct numerical answer.