We are interested in the supersonic flow of air through a convergent-divergent nozzle having a circular cross-sectional area, A, that varies with axial distance from the throat, x, according to the formula

A = C1 + x2;  -0.5 < x < 0.5

where A is in m2 and x is in m C1 is a constant which is different for each where A is in m and x is in m.  C1 is a constant which is different for each student. The stagnation pressure p_o at the inlet is given. The stagnation temperature T_o at the inlet is 300 K. The static pressure p at the exit is also given given. 

We will calculate the Mach number, pressure and temperature distribution in the FLUENT the nozzle using FLUENT and compare the solution to quasi-1D nozzle flow results. The Reynolds number for this high-speed flow is large. Use an inviscid flow model.