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Author: Rajesh Bhaskaran, Cornell University {color:#cc0000}{*}Problem Specification{*}{color} [1. Create Geometry in GAMBIT|FLUENT - Compressible Flow in a Nozzle- Step 1] [2. Mesh Geometry in GAMBIT|FLUENT - Compressible Flow in a Nozzle- Step 2] [3. Specify Boundary Types in GAMBIT|FLUENT - Compressible Flow in a Nozzle- Step 3] [4. Set Up Problem in FLUENT|FLUENT - Compressible Flow in a Nozzle- Step 4] [5. Solve\!|FLUENT - Compressible Flow in a Nozzle- Step 5] [6. Analyze Results|FLUENT - Compressible Flow in a Nozzle- Step 6] [7. Refine Mesh|FLUENT - Compressible Flow in a Nozzle- Step 7] [Problem 1|FLUENT - Compressible Flow in a Nozzle- Problem 1] [Problem 2|FLUENT - Compressible Flow in a Nozzle- Problem 2] {panel} h2. Problem Specification !nozzle2.jpg! Consider air flowing at high-speed 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 = 0.1 + x{^}2^; \-0.5 < x < 0.5 where _A_ is in square meters and _x_ is in meters. The stagnation pressure _p{_}{_}{~}o{~}_ at the inlet is 101,325 Pa. The stagnation temperature _T{_}{_}{~}o{~}_ at the inlet is 300 K. The static pressure _p_ at the exit is 3,738.9 Pa. We will calculate the Mach number, pressure and temperature distribution in the nozzle using FLUENT and compare the solution to quasi-1D nozzle flow results. The Reynolds number for this high-speed flow is large. So we expect viscous effects to be confined to a small region close to the wall. So it is reasonable to model the flow as inviscid. Go to [Step 1: Create Geometry in GAMBIT|FLUENT - Compressible Flow in a Nozzle- Step 1] [See and rate the complete Learning Module|FLUENT - Compressible Flow in a Nozzle] [Go to all FLUENT Learning Modules|FLUENT Learning Modules]University Problem Specification |
Problem Specification
Consider air flowing at high-speed 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 = 0.1 + x2; -0.5 < x < 0.5
where A is in square meters and x is in meters. The stagnation pressure po at the inlet is 101,325 Pa. The stagnation temperature To at the inlet is 300 K. The static pressure p at the exit is 3,738.9 Pa. We will calculate the Mach number, pressure and temperature distribution in the nozzle using FLUENT and compare the solution to quasi-1D nozzle flow results. The Reynolds number for this high-speed flow is large. So we expect viscous effects to be confined to a small region close to the wall. So it is reasonable to model the flow as inviscid.
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