[sourena14714]

hi
i am trying to simulate a pitching airfoil and want to draw lift coefficient as angle of attack like an article but i cant.anyone coulde help pls?
i use this udf:
/************************************************** *****
UDF to define the angular velocity of the oscillating wing
************************************************** ******
omega= pitching rate
thetamax= pitching amplitude
w= angular frequency, 2*pi*f
************************************************** *****/
#include "udf.h"
DEFINE_TRANSIENT_PROFILE(angular_velocity,time)
{
real omega;
double thetamax=15*M_PI/180 , w=2*14*0.1/0.15;
omega =-1*thetamax*(w)*cos(w*time);
return omega;
}