[Jishan Ahmed]

#include "udf.h"
#include "math.h"
#include "sg_udms.h"
#define debye 0.001
#define rhomax 0.0008
#define phimax 5000
#define sigma 0.003
#define rholoc 0.5
enum {
phi,
rho
};
enum {
Ex,
Ey,
Fx,
Fy,
Fm
};

DEFINE_ADJUST(udf_adjust, domain)
{
Thread *t;
cell_t c;
thread_loop_c(t,domain)
{
begin_c_loop(c,t)
{
C_UDMI(c,t,Ex)=-C_UDSI_G(c,t,phi)[0];
C_UDMI(c,t,Ey)=-C_UDSI_G(c,t,phi)[1];
}
end_c_loop(c,t)
}
}

DEFINE_SOURCE(rho_source, c, t, dS, eqn)
{
real source;
source=-pow(debye,-2)*C_UDSI(c,t,rho);
dS[eqn]=-pow(debye,-2);
return source;
}

DEFINE_SOURCE(X_Source, c, t, dS, eqn)
{
real Sourcex;
Sourcex=-rhomax*phimax*C_UDSI(c,t,rho)*C_UDSI_G(c,t,phi)[0];
dS[eqn]=-rhomax*phimax;
C_UDMI(c,t,Fx)=Sourcex;
return Sourcex;
}

DEFINE_SOURCE(Y_Source, c, t, dS, eqn)
{
real Sourcey;
Sourcey=-rhomax*phimax*C_UDSI(c,t,rho)*C_UDSI_G(c,t,phi)[1];
dS[eqn]=-rhomax*phimax;
C_UDMI(c,t,Fy)=Sourcey;
C_UDMI(c,t,Fm)=sqrt(C_UDMI(c,t,Fx)*C_UDMI(c,t,Fx)+ C_UDMI(c,t,Fy)*C_UDMI(c,t,Fy));
return Sourcey;
}

DEFINE_PROFILE(rho_profile,thread,i)
{
float r[3];
float x;
real xloc;
face_t f;
begin_f_loop(f,thread)
{
F_CENTROID(r,f,thread);
xloc = r[0];
F_PROFILE(f,thread,i)=exp(-pow((xloc-rholoc),2)/(2*pow(sigma,2)));
}
end_f_loop(f,thread)
}

this is a udf by
Modeling of Dielectric-Barrier Discharge Actuator
Implementation, validation and generalization of an electrostatic model
A. Bouchmal

how to implement this on an airfoil (noting its cambered profile) study. Specially the changes in cell zone boundary conditions or any other.
I tried my best to my knowledge.

[Yijun Lu]

I met the same problem. I complied the UDF in fluent, but when I define the number of UDM and UDS, which are 5 and 2 respectively, and x, y momentum in the source term, errors occur after calculation and "fluent process cannot be ...".

[Jishan Ahmed]

Solved your problem?

[Yijun Lu]

Originally Posted by Jishan Ahmed

Solved your problem?

Not yet!

Here are the problems I met.

When I complied this UDF in FLUENT successfully, I take the following steps:

(1) define the numbers of UDM and UDS, which are 5 and 2 respectively.

(2) add the x-momentum and y-mom sources term in cell zone condition

the next step is adding the User scalar 0 and 1 with rho_profile and rho_source, which I cannot be sure.

Then errors occur after clicking calculation

By the way, the author of this UDF uses it to solve the body force of the plasma only, not on airfoil. So may be we can solve the UDF inplementation on plasma firstly, and then on airfoil?