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Showing results 1 to 6 of 6 Search took 0.00 seconds. Search: Posts Made By: mingersai

Forum: Main CFD Forum January 13, 2012, 15:38

Replies: 13 why lift coefficients don't converge at high angle of attacks? Views: 6,706 Posted By mingersai Thanks for your guys discussion~ I learnt a lot... Thanks for your guys discussion~ I learnt a lot from this ~ :):):)

Forum: Main CFD Forum January 12, 2012, 15:12

Replies: 13 why lift coefficients don't converge at high angle of attacks? Views: 6,706 Posted By mingersai Thank you very much ! It's very helpful~! Thank you very much ! It's very helpful~!

Forum: Main CFD Forum January 11, 2012, 18:41

Replies: 13 why lift coefficients don't converge at high angle of attacks? Views: 6,706 Posted By mingersai Thanks~ I should read more about airfoil... Thanks~ I should read more about airfoil stalling... I don't really understand how experimental people measure Lift and Drag at this angle.... I found some experimental results for comparison and...

Forum: Main CFD Forum January 11, 2012, 17:14

Replies: 13 why lift coefficients don't converge at high angle of attacks? Views: 6,706 Posted By mingersai Thanks for all your replies. :o:) I'm using... Thanks for all your replies. :o:) I'm using unstructured mesh, and transient formulation is implicit. I had changed to run for steady state solution, I got converged solution ...

Forum: Main CFD Forum January 11, 2012, 14:04

Replies: 13 why lift coefficients don't converge at high angle of attacks? Views: 6,706 Posted By mingersai Hi, Thanks for replying~ Does it mean this... Hi, Thanks for replying~ Does it mean this simulation result is reasonable? I found some experiment results for this angle of attack, I'm not sure how experiment people pick up the values for lift...

Forum: Main CFD Forum January 11, 2012, 12:46

Replies: 13 why lift coefficients don't converge at high angle of attacks? Views: 6,706 Posted By mingersai why lift coefficients don't converge at high angle of attacks? Dear Friends I'm running simulation on a NACA 64 210 airfoil with k-omega sst model with Re = 2.6 E6 . The chord length is 1m. Angle of Attack ranges from 0 to 20. I'm changing the inlet...

Showing results 1 to 6 of 6

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