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Mesh to validat result of airfoil S1223

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Old   December 12, 2017, 16:54
Default Mesh to validat result of airfoil S1223
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Josť Mantovani
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Hello everyone!


The days I'm trying to get the experimental result for my numerical solution. Basically I'm doing an external flow simulation around an S1223 airfoil. I have tried several different meshes, all in vain, differently for NACA airfoils (which are relatively symmetrical) with a basic mesh converge the value of my solution with the experimental value. I would like some help or if anyone can give me some tips on how to improve my results. The experimental value of Cl for airfoil S1223 is, Cl = 2.23. But with my mesh the best I got was Cl = 1.09 (which sucks and does not suit me), yet the contours show expected physical results (low pressure on top and bottom on bottom, anyway ...), but the numerical result goes a long way. I believe the main problem is the mesh (and it is ...). Just to know, I'm using ANSYS software and its FLUENT solver. I'm doing everything by the Workbench, because that's where I know ... Sirs help me, I'm going crazy! LOL

P.S.: I am using student package, a very refined mesh does not serve me, remembering the restriction of the package and my computer, so it can not be a prohibitive mesh.

Thanks for attention and helping guys!
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Old   December 13, 2017, 05:56
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Josť Mantovani
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Hello everyone!


The days I'm trying to get the experimental result for my numerical solution. Basically I'm doing an external flow simulation around an S1223 airfoil. I have tried several different meshes, all in vain, differently for NACA airfoils (which are relatively symmetrical) with a basic mesh converge the value of my solution with the experimental value. I would like some help or if anyone can give me some tips on how to improve my results. The experimental value of Cl for airfoil S1223 is, Cl = 2.23. But with my mesh the best I got was Cl = 1.09 (which sucks and does not suit me), yet the contours show expected physical results (low pressure on top and bottom on bottom, anyway ...), but the numerical result goes a long way. I believe the main problem is the mesh (and it is ...). Just to know, I'm using ANSYS software and its FLUENT solver. I'm doing everything by the Workbench, because that's where I know ... Sirs help me, I'm going crazy! LOL

P.S.: I am using student package, a very refined mesh does not serve me, remembering the restriction of the package and my computer, so it can not be a prohibitive mesh.

Thanks for attention and helping guys![/QUOTE]
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Old   March 3, 2021, 15:39
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Aideal Zohary
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Hi, this is an old thread. But if anyone is still interested to run a simulation on the S1223 airfoil, please take a look at:

Numerical Investigation on the Pressure Drag of Some Low-Speed Airfoils for UAV Application.
https://doi.org/10.37934/cfdl.13.2.2948

Unsteady 3-equation k omega intermittency SST was used. Good comparison with XFOIL and experimental data. Transition features also shown through cf and cp plots.
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Old   September 2, 2021, 02:06
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Aideal Zohary
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Quote:
Originally Posted by AidealZohary View Post
Hi, this is an old thread. But if anyone is still interested to run a simulation on the S1223 airfoil, please take a look at:

Numerical Investigation on the Pressure Drag of Some Low-Speed Airfoils for UAV Application.
https://doi.org/10.37934/cfdl.13.2.2948

Unsteady 3-equation k omega intermittency SST was used. Good comparison with XFOIL and experimental data. Transition features also shown through cf and cp plots.
Learn how I designed my mesh here:

https://www.youtube.com/watch?v=qZRqBu9Ss2U
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