Question 19 (5 points) The combustor discharge into a turbine nozzle has a total temperature of T12=2200 K and an axial Mach number of M = 0.65. The static temperature is T = 2040 K and the nozzle exit flow angle is a2 = 65. Determine the exit absolute Mach number, M2. Assume y = 1.33 and cp = 1157 J/kg-K. (Hint: see Example 10.1) M2 = 1.06 M2 = 1.27 M2=1.85 M2 = 2.82 Question 20 (5 points) What is the maximum practical exit flow angle for a nozzle? a2, max = 65 a2,max=70 = a2, max 75 a2, max a2, max 80