|January 20, 2014, 02:51||
not getting converges Cd, Cl at high AOA
Join Date: Dec 2013
Location: Dhaka, Bangladesh
Posts: 7Rep Power: 3
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.
|cd not converged, drag coefficient, flow over airfoil, supercritical airfoil|
|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 05:12|
|grids around airfoils at high aoa||uygun||Main CFD Forum||9||October 11, 2002 08:30|
|Flow solutions over airfoils at high aoa||UYGUN||CFX||0||October 8, 2002 15:23|
|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 06:26|