|June 23, 2006, 01:10||
setting reference values to find Cd, Cl, Cm (3D)
I'm trying to simulate a small experimental rocket (1,5m tall) in order t oget its aerodynamic coeff (Cd, Cl, and Cm at low angle of attack : 1°).
The problem is that I have a Cd=2500 !!
I think that may come from the ref. values...
Here is my mesh : http://img145.imageshack.us/img145/9...illage15dv.png
What sould I fill in area ? The cross area, or total area ? And for lenght... ?
I've computed from my environment (a half cylinder, in pressure far filed).
Any help is welcome !!
Thank you !!
|Thread||Thread Starter||Forum||Replies||Last Post|
|Second Derivative Zero - Boundary Condition||fu-ki-pa||OpenFOAM||10||May 1, 2014 16:26|
|compile error about FJMPI||chiven||OpenFOAM Installation||11||March 31, 2010 06:27|
|Parallel processing problem with mpich||nzy102||OpenFOAM Running, Solving & CFD||14||October 18, 2007 00:05|
|G95 + CGNS||Bruno||Main CFD Forum||1||January 30, 2007 01:34|
|Reference Values Help||Sham||FLUENT||0||February 26, 2005 09:43|