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[ICEM] Wrapping mesh around NACA0012

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Old   May 13, 2012, 17:38
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Sijal Ahmed Memon (turboenginner@gmail.com)
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give me boundary conditions
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Old   May 13, 2012, 17:39
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boundary conditions:
1-CURVES ----> wall
2-INLET -----> velocity inlet: velocity = 90 for zero angle of attack in X-direction (it can be found for other angles of attack)
3-OUTLET ----> pressure outlet (atmosphere pressure)
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Old   May 13, 2012, 17:49
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can you show the convergence plot. whats the mach no. for this simulation?
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Old   May 13, 2012, 17:52
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what do u mean?
I just set the velocity at INLET and the fluid is air "density=ideal gas, viscosity=sutherland"
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Old   May 13, 2012, 17:53
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there is no option to set Mach No.
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Old   May 14, 2012, 06:49
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The outer boundary shall be modeled using Farfield BC. And, ofcourse you need Mach no for this.

There was tutorial on NACA 0012 Airfoil, with some AoA, using Fluent. You shall go through that for reference.

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what do u mean?
I just set the velocity at INLET and the fluid is air "density=ideal gas, viscosity=sutherland"
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Old   May 14, 2012, 10:24
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what is the difference if I use INLET and OUTLET boundary conditions instead of farfield?
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Old   May 15, 2012, 04:14
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To quote from FLUENT Manual:

Velocity Inlet BC:
" In this case, the total (or stagnation) pressure is not fixed but will rise (in response to the computed static pressure) to whatever value is necessary to provide the prescribed velocity distribution.

This boundary condition is intended for incompressible flows, and its use in compressible flows will lead to a nonphysical result because it allows stagnation conditions to float to any level. "

Based on the information provided in the thread, I had assumed that you are trying to solve the compressible flow problem. In the external flow problems, the stagnation properties remain constant.

Kindly refer to FLUENT Manual for selecting appropriate BC for the simulations.

Hope this helps for your project.
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Old   May 15, 2012, 09:42
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Quote:
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check this mesh
How do you associate green edges to the curves of the wing? So, the edges coincide with the curves of the wing?
Attached Images
File Type: png naca0012.png (5.4 KB, 11 views)
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Old   May 15, 2012, 09:52
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you're da man!
thanks
Im doing Compressible (Air, density=ideal gas, viscosity=sutherland)


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Originally Posted by E63 AMG View Post
To quote from FLUENT Manual:

Velocity Inlet BC:
" In this case, the total (or stagnation) pressure is not fixed but will rise (in response to the computed static pressure) to whatever value is necessary to provide the prescribed velocity distribution.

This boundary condition is intended for incompressible flows, and its use in compressible flows will lead to a nonphysical result because it allows stagnation conditions to float to any level. "

Based on the information provided in the thread, I had assumed that you are trying to solve the compressible flow problem. In the external flow problems, the stagnation properties remain constant.

Kindly refer to FLUENT Manual for selecting appropriate BC for the simulations.

Hope this helps for your project.
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Old   May 15, 2012, 09:54
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I use Edit Edge-->Automatic Linear, exactly as Simon says in his tutorial

how am I supposed to do that? any better ideas? how about the leading edge facet?

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How do you associate green edges to the curves of the wing? So, the edges coincide with the curves of the wing?
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