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CFD on Wing with winglets

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Old   January 9, 2020, 09:55
Default CFD on Wing with winglets
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Hammad
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Help Required!!

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We are trying to perform cfd on ONERA M6 wing with different winglet configurations at various AOA. The problem is that the solution converges at 3 and 4 AOA but never converges for angles greater than 4 degrees. I have attached the residuals , lift and drag for 4,5 and 6 AOA.

Boundary Conditions:
1. Mach Number = 0.8395
2. Temperature = 460 R
3. Pressure = 45.82899 psi
4. AOA = 0 to 10

Mesh:
1. Total elements = 0.9 million
2. Skewness = 0.2
3. Unstructured tetrahedral

Solver: Fluent
1. spalart-allmaras with energy on
2. Steady
Attached Images
File Type: png lift at 3 AOA.PNG (9.6 KB, 11 views)
File Type: png lift at 4 AOA.PNG (9.9 KB, 13 views)
File Type: png lift at 6 AOA.PNG (10.7 KB, 13 views)
File Type: png Residuals at 3 AOA.PNG (18.2 KB, 14 views)
File Type: png Residuals at 5 AOA.PNG (22.3 KB, 12 views)
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Old   February 7, 2020, 23:15
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Suman Dathathreya
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Hi,
Try running it for more iterations and then observe the Cl and CD graph becomes a straight line, then you can consider that the CL and CD values are converged
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