 |
 |
 |
|
|
|
[Sponsors] | ||||
January 20, 2014, 02:51
|
not getting converges Cd, Cl at high AOA
|
#1 |
|
New Member
rishad rizwan
Join Date: Dec 2013
Location: Dhaka, Bangladesh
Posts: 7
Rep Power: 13  |
hello all ,
i am running a simulation of super critical airfoil at transonic speed. I am getting converged results at AOA upto 4 degree which agree well with the experimental results, but at AOA 5 to 9 degree the results (Cd,Cl,Cm) becomes periodic....then again at AOA 10,11,12..results are converging..... I'm doing steady state pressure based solution with S-A model. can anyone tell me please whether it's natural or due to any error in my modeling ? thanks in advance for your reply. |
|
|
|
|
 |
| Tags |
| cd not converged, drag coefficient, flow over airfoil, supercritical airfoil |
|
|
Similar Threads
|
||||
| Thread | Thread Starter | Forum | Replies | Last Post |
| simulation of airfoil at high AOA | hsnu84053 | FLUENT | 0 | January 26, 2007 22:34 |
| Multicomponent fluid | Andrea | CFX | 2 | October 11, 2004 06:12 |
| grids around airfoils at high aoa | uygun | Main CFD Forum | 9 | October 11, 2002 09:30 |
| Flow solutions over airfoils at high aoa | UYGUN | CFX | 0 | October 8, 2002 16:23 |
| A conference in air load /flight simulation/flight test/wind tunnel test/aero modeling for high AOA | cimsi | Main CFD Forum | 0 | September 17, 1998 07:26 |
Linear Mode
