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Search took 0.00 seconds. Search: Posts Made By: Nick R
Forum: CFX July 22, 2011, 00:03
Replies: 29
Views: 6,302
Posted By Nick R
I see. Excellent. I'll contact you.

I see. Excellent. I'll contact you.
Forum: CFX July 21, 2011, 23:32
Replies: 29
Views: 6,302
Posted By Nick R
Sounds very interesting and quite complicated....

Sounds very interesting and quite complicated. Kudos to you! How did the unstalled naca0012 past 8 (100k) fair in terms of lift coefficient at higher angles compared to experiments?
Forum: CFX July 21, 2011, 04:05
Replies: 29
Views: 6,302
Posted By Nick R
Thanks for the paper and the comments. It must...

Thanks for the paper and the comments. It must have been a lot of hard work. So from what I understand your NACA 0012 stalled past 8, is that why you didn't include the results from that point...
Forum: CFX July 19, 2011, 23:12
Replies: 29
Views: 6,302
Posted By Nick R
Reynolds is 122000. Span/chord = 8 no trips were...

Reynolds is 122000. Span/chord = 8 no trips were used...no two bumps is observed in lift diagram ...force measurements and pressure measurements were both done and in good agreement in terms of lift...
Forum: CFX July 19, 2011, 21:37
Replies: 29
Views: 6,302
Posted By Nick R
I know it's working reasonably well up to 7...

I know it's working reasonably well up to 7 degrees AOA based on my own wind tunnel experiments, literature and also xfoil but past this angle it goes into stall which it's not supposed to-stall...
Forum: CFX July 19, 2011, 20:26
Replies: 29
Views: 6,302
Posted By Nick R
Thanks for the suggestions. I've done yplus...

Thanks for the suggestions. I've done yplus sensitivity study but it hasn't changed the cf distribution. I'll do it again just to double check. If gamma theta is available as an option for SA in cfx...
Forum: CFX July 19, 2011, 04:48
Replies: 29
Views: 6,302
Posted By Nick R
Hi Martin, I ran the simulation using slip...

Hi Martin,

I ran the simulation using slip walls and convergence was problematic (residuals oscillated a lot) plus the pressure distribution on the foil was wrong.
At 4 deg AOA using no-slip...
Forum: CFX July 15, 2011, 08:32
Replies: 29
Views: 6,302
Posted By Nick R
Thanks for the feedback. I wonder whether other...

Thanks for the feedback. I wonder whether other solvers perform better with the model than cfx.
Forum: CFX July 15, 2011, 08:21
Replies: 29
Views: 6,302
Posted By Nick R
Hi Josh I'm looking forward to the paper....

Hi Josh

I'm looking forward to the paper. The issue I'm struggling with is that the foil goes into stall a few degrees too early and at lower lift coefficient values than experiments. It's a thick...
Forum: CFX July 12, 2011, 23:58
Replies: 29
Views: 6,302
Posted By Nick R
Hi Is there a chance I could have an email...

Hi

Is there a chance I could have an email address. I'm using this simulation for my graduate degree so it may be best not to post results here. Thanks for your attention. You may wish to send a...
Forum: CFX June 18, 2011, 12:12
Replies: 29
Views: 6,302
Posted By Nick R
Gamma Theta model and underpredicted lift

Hi All,

I've been trying to simulate incomressible flow over a thick airfoil NACA0020 at transitional reynolds numbers using the gamma theta model.
Although the transition onset and pressure...
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