CFD on Wing with winglets

hammad66 · January 9, 2020, 10:55

Help Required!!

See Attachements

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

dnsuman · February 8, 2020, 00:15

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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February 8, 2020, 00:15		#2
dnsuman New Member Suman Dathathreya Join Date: Jul 2018 Posts: 13 Rep Power: 8	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