[hammad66]

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]

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