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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 po at the inlet is given. The stagnation temperature To 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.
i want help
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