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{alias:nozzle}
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Author: Rajesh Bhaskaran, Cornell
University

Problem Specification
1. Create Geometry in GAMBIT
2. Mesh Geometry in GAMBIT
3. Specify Boundary Types in GAMBIT
4. Set Up Problem in FLUENT
5. Solve!
6. Analyze Results
7. Refine Mesh
Problem 1
Problem 2

Problem Specification

Image Removed

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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{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]
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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]

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