|September 16, 2009, 03:55||
Referece Area of 2D Airfoil
Join Date: Apr 2009
Posts: 17Rep Power: 8
can somebody tell me how the reference area is determined in OF 1.5? Until now I used the chordlength * mesh-extrusion in z direction. But I am not sure as my calculated Cd and Cl values are defnitely wrong.
|September 16, 2009, 16:42||
Join Date: Jun 2009
Location: Colorado, USA
Posts: 112Rep Power: 8
My impression was that openfoam calculates the forces on all faces of the object and vector sums them. Then divides the drag vector and lift vectors by density, U^2 and the reference area that you specified to get Cd and Cl.
I believe chord_length * wing_length is the standard equation for wing reference area.
For objects other than wings, the reference area for drag is usually the area that the wind 'sees', but when it comes to wings, its the same area as for lift.
I don't think it's your reference_area that's wrong, I think it's the forces coming out of the simulation
|Thread||Thread Starter||Forum||Replies||Last Post|
|Low Speed Airfoil||Mancusi||FLUENT||7||April 3, 2014 06:11|
|Modeling Backflow for a 3D Airfoil (Wing of Finite Span)||Josh||CFX||9||August 18, 2009 11:31|
|Airfoil boundary condition||Frank||Main CFD Forum||1||April 21, 2008 18:36|
|CFX Solver Memory Error||mike||CFX||1||March 19, 2008 08:22|
|Storing Surface Area of each cell in a file?||Markus Alzon||FLUENT||0||June 21, 2007 08:38|