|July 11, 2013, 03:33||
Viscous flow over naca0012 airfoil
Join Date: Jun 2013
Posts: 30Rep Power: 4
I am new to CFD and SU2. I had gone through the tutorials in the SU2 website.
I am trying to find the Cl and Cd for flow over NACA0012 airfoil (using the same mesh given in test cases for inv_naca0012) .
For angle of attack = 0 deg, i get
Cl= - 0.001625
The Cd value is significantly high compared to NACA report which is around Cd=0.006.
The configuration file is attached ( in txt format). Kindly tell me what are the mistakes I have done.
Last edited by shsreekanth; July 15, 2013 at 13:34.
|August 16, 2013, 01:48||
Join Date: Jan 2013
Location: Long Beach, CA
Posts: 342Rep Power: 6
To run a RANS problem you need an a-priori adapted grid in the boundary layer. You will find those grids in the TestCases/rans folder
Thanks for using SU2,
|Thread||Thread Starter||Forum||Replies||Last Post|
|Simulating flow past airfoil with different AOA||ramin||FLUENT||4||April 22, 2015 13:09|
|Supersonic flow over an airfoil. FLUENT Lift don't match up with Shock Expansion Tech||enriccasas||FLUENT||1||August 21, 2013 06:43|
|Problem with airfoil shape optimization||robyTKD||SU2 Shape Design||6||June 13, 2013 19:13|
|energising the flow over an airfoil using synthetic jets||aerojeeva21||FLUENT||5||March 4, 2011 08:47|
|simulation of a turbulent flow on airfoil||Dante||FLUENT||3||June 8, 2007 14:54|