[rsarma]

Hi all,

Is there a way to calculate the lift/drag coefficient over e.g. a wing via Fluent UDF? Please see part of the code below:

begin_f_loop(f,t)
{
F_AREA(A,f,t);
PF_y+ = F_P(f,t)*A[1];
}
end_f_loop(f,t)

I thought the variable PF_y divided by the dynamic pressure, should give me the lift force in the respective direction. But the result does not match with the lift monitor value reported by FLUENT. Please let me know if you know of this issue.

Kind Regards,
RS