a) Downstream of the throat the area of the nozzle increases. At the nozzle exit the Mach number is 2.5. What is the nozzle diameter (in cm) at the exit ? b) At the location where the nozzle diameter is 25 cm, what is the gas velocity? c) If the air has a stagnation pressure (po) of 60 atm and a stagnation temperature of 1200 K upstream of the throat, what is the mass flow rate in kg/sec ? Hint: use Fliegner's formula (below) that is on p. 71 of our textbook by Hill and Peterson. m2 = [0.040 (kg/s) Pa‍¹ m²² K1/2] (Poz A2*) (T02)-1/2 Location "2" is any location, since the mass/sec is the same at all streamwise x- locations. Note: po, To and A* are the same values at all x-locations.