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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.
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tabular method
If all states are measured by appropriate sensors and interfaced to the flight control computer then allthe states may be fed back and there is no restriction on the choice of K. S
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