 |
 |
 |
|
|
|
[Sponsors] | ||||
February 18, 2010, 11:36
|
problem with stall in naca 0012 airfoil
|
#1 |
|
Member
thanos
Join Date: Oct 2009
Posts: 30
Rep Power: 17  |
Hello!
I try to simulate naca 0012 in a Re=2*10^6 , u=40m/s and c=1. I use Spalart-allamaras turbulence model. For this Re number the airfoil stalls in angle of attack=14. I have made many different meshes with y+<3 but none of them has been effective. The problem i face is that although for angles up to 14 i calculate Cl with minimun divergence, in bigger angles (15,16...) the Cl continues to increase instead of falling. Is anything that i am doing wrong? Please help! Thanks in advance! |
|
|
|
|
 |
| Thread Tools | Search this Thread |
| Display Modes | |
|
|
Similar Threads
|
||||
| Thread | Thread Starter | Forum | Replies | Last Post |
| [Commercial meshers] Naca 0012 airfoil | naveen | OpenFOAM Meshing & Mesh Conversion | 7 | April 14, 2011 11:03 |
| [GAMBIT] Meshing airfoil using .dat file problem | creggie | ANSYS Meshing & Geometry | 10 | June 27, 2010 19:24 |
| airfoil optimizer chain with drag problem | Arnolm | OpenFOAM Running, Solving & CFD | 2 | October 18, 2009 13:43 |
| NACA 0012 | Ihab Sraj | CFX | 6 | August 29, 2006 10:35 |
| Drag predicion for a NACA 0012 airfoil | Peter Giannakopoulos | FLUENT | 7 | March 9, 2004 15:32 |
Linear Mode
