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kindly help me .. i have and error at line number 147..

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Old   February 10, 2019, 11:25
Default kindly help me .. i have and error at line number 147..
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m zubair
Join Date: Feb 2019
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when i try to build into fluent i got the following error
src\silo.c(147) : error C2440: '=' : cannot convert from 'Profile' to 'float'
please rectify this udf code.. it will be great help for me .

#include "udf.h"
#include "dynamesh_tools.h"

#define nozzle_tid 12 /* Zone ID of nozzle exit */
#define missile_tid 14 /* Zone ID of missile wall */
#define moving_fluid_id 2 /* Zone ID of fluid surrounding the missile */

#define t_liftoff 0.1 /* Time at which to allow lift-off (sec) */
#define g_c 9.81 /* Gravity acceleration */
#define initial_mass 200.0 /* Initial mass of the rocket (kg) */
#define burn_rate 0.0 /* Fuel burn rate (kg/sec) */
#define pi 4.0*atan(1.0)

float U_sum; /* Sum of inlet U velocity */
float V_sum; /* Sum of inlet V velocity */
float W_sum; /* Sum of inlet W velocity */
float A_sum; /* Sum of facet areas */
float P_sum; /* Sum of face pressure */
float P_i; /* Pressure on face i */
float A_i; /* Area of face i */
float U_i; /* U velocity on face i */
float V_i; /* V velocity on face i */
float W_i; /* W velocity on face i */
float A[3]; /* Area vector of face i */
float VA_sum; /* Sum of velocity times area */
float VEL_i; /* Velocity magnitude on face i */
float V_avg; /* Average velocity */
float V_e; /* Nozzle exit velocity relative to missile */
float Pthrust; /* Thrust due to pressure */
float Mthrust; /* Thrust due to momentum */
float MDOT; /* Mass flow rate from the missile */
float Vmiss[3]; /* Missile velocity vector */
/*float Umiss;*/ /* Missile x velocity */
/*float Vmiss;*/ /* Missile y or r velocity */
/*float Wmiss;*/ /* Missile z velocity (zero for 2-D) */


Domain *domain;
face_t f; /* Nozzle faces */
Thread *t; /* Nozzle thread */
Dynamic_Thread *tmiss; /* Missile wall thread */

DEFINE_SDOF_PROPERTIES(launch, prop, dt, time, dtime)
{

/* Define the mass and moments of inertia */
prop[SDOF_MASS] = initial_mass - (burn_rate * time);
prop[SDOF_IXX] = 0.0;
prop[SDOF_IYY] = 0.0;
prop[SDOF_IZZ] = 0.0;

/* Define ejector moments */
prop[SDOF_LOAD_M_X] = 0.;
prop[SDOF_LOAD_M_Y] = 0.;
prop[SDOF_LOAD_M_Z] = 0.;

/* Calculate rocket thrust and assign to X ejector force.*/
U_sum = 0.0;
V_sum = 0.0;
W_sum = 0.0;
A_sum = 0.0;
P_sum = 0.0;
Pthrust = 0.0;

A_sum = 0.0;
VA_sum = 0.0;
Pthrust = 0.0;
Mthrust = 0.0;

/* Lookup thread values */
domain = Get_Domain(1);
t = Lookup_Thread(domain, nozzle_tid);
tmiss = THREAD_DT(Lookup_Thread(domain, missile_tid)); /* Missile wall */

/* Compute area-weighted average exit velocity */

Message("\n ****************************************");
Message("\n ******* Nozzle Exit Conditions *******");
Message("\n ****************************************");


/* Visit each face on the inlet and add up Vx, Vr, Area, and Pressure */
begin_f_loop (f, t)
{
/* Retrieve the area vector of the current face */
F_AREA(A, f, t);

/* Message("\n check 1");*/

/* Calculate the area of current face */
A_i = NV_MAG(A);

/*Message("\n check 2");*/

/* Retrieve the pressure on the current face */
P_i = F_P(f,t);

/*Message("\n check 3");*/

U_i = F_U(f,t); /* U Velocity on the current face */
V_i = F_V(f,t); /* V velocity on the current face */

#if RP_2D
W_i = 0.0; /* W Velocity (2D) */
#else
W_i = F_W(f, t); /* W Velocity (3D) */
#endif

VEL_i = sqrt(U_i*U_i+V_i*V_i+W_i*W_i); /* Velocity magnitude */


A_sum += A_i; /* Increment the face area */
VA_sum += VEL_i * A_i; /* Increment the VxA */
Pthrust += P_i * A_i; /* Increment the pressure force */

}

end_f_loop (f, t)

#if RP_2D
if(rp_axi)
{A_sum *= 2*pi;
VA_sum *= 2*pi;
Pthrust *= 2*pi;}
#endif

V_avg = VA_sum / A_sum;

Message("\n -> Current Time = %f sec", time);
Message("\n -> Liftoff time = %f sec", t_liftoff);
Message("\n -> Total inlet area = %f m2", A_sum);
Message("\n -> = %f ft2", A_sum / (0.3048 * 0.3048));
Message("\n");
Message("\n -> Average Velocity = %f m/sec", V_avg);
Message("\n = %f ft/sec", V_avg / 0.3048);
Message("\n");
Message("\n -> Average Inlet Pressure = %f Pa", Pthrust / A_sum);
Message("\n = %f psi", Pthrust / A_sum * (14.7/101325.));

/* OBTAIN THE MASS FLOW RATE ACROSS THE INLET */

MDOT = 0.0;

/* Obtain the mass flow rate if inlet is mass flow type */
if (THREAD_VAR(t).mfi.flow_spec == MASS_FLOW_TYPE)
{
MDOT = THREAD_VAR(t).mfi.mass_flow;

Message("\n -> Mass Flow Rate = %f kg/sec", MDOT);
Message("\n -> = %f lbm/sec", MDOT / 2.205);
}

else
{

Message("\n NOW INSIDE UNTESTED PORTION OF THE UDF");


/*
THE FOLLOWING HAS NOT BEEN TESTED YET!!
*/

/* if (IS_PROFILE (THREAD_VAR (t).mfi.mass_flux))
{
Message("\n====================================");
Message("\n MDOT HAS BEEN SPECIFIED AS PROFILE");
Message("\n Beginning face loop.");

begin_f_loop (f, t)
{
mass_flux = NV_MAG (F_AREA_CACHE (f, t))
* F_VAR (f, t, THREAD_VAR (t).mfi.mass_flux);

Message("\n MASS FLOW RATE FOUND.\n");

}
end_f_loop (f, t)

Message("\n VALUE OF MDOT = %f", MDOT);
Message("\n====================================");
}
else
{

Message("\n LOOKING UP MASS FLOW RATE (NOT PROFILE)\n");

mass_flux = THREAD_VAR(t).mfi.mass_flux.constant * A_sum;
MDOT = A_sum * mass_flux;

Message("\n Finished calculating for non profile case. Results:");
Message("\n mass_flux = %f", THREAD_VAR(t).mfi.mass_flux.constant);
Message("\n A_sum = %f", A_sum);
Message("\n MDOT = %f", MDOT);


}
*/


/* END OF UNTESTED SECTION */


/*
#if RP_2D
if (rp_axi) MDOT *= 2.0 * pi;
#endif
*/
}


/* COMPUTE ROCKET THRUST AS (Avg Velocity) * (mass flow rate)

force = V_avg * F_VAR (0, t, THREAD_VAR(t).mfi.mass_flux) / total_;
*/



/* OBTAIN THE CURRENT MISSILE VELOCITY */
if(time < t_liftoff)
{DT_VEL_CG(tmiss)[0] = 0.0;}
/* {Umiss = DT_VEL_CG(tmiss)[0];} */
/* Vmiss[0]=DT_VEL_CG(tmiss)[0];
else
{DT_VEL_CG(tmiss)[0] = 0.0;}

Umiss = DT_VEL_CG(tmiss)[0]; */


Message("\n ***************************************");
Message("\n ******** Thrust / Velocity *********");
Message("\n ***************************************");


Message("\n -> Missile Velocity = %f m/sec", Vmiss[0]);
Message("\n -> = %f ft/sec", Vmiss[0]/0.3048);

#if RP_2D
if (rp_axi)
{
Message("\n -> Missile Velocity Axial = %f m/sec", DT_VEL_CG(tmiss)[0]);
Message("\n -> = %f ft/sec", DT_VEL_CG(tmiss)[0]/0.3048);

Message("\n -> Missile Velocity Radial = %f m/sec", DT_VEL_CG(tmiss)[1]);
Message("\n -> = %f ft/sec", DT_VEL_CG(tmiss)[1]/0.3048);
}
else
{
Message("\n -> Missile Velocity (X) = %f m/sec", DT_VEL_CG(tmiss)[0]);
Message("\n -> = %f ft/sec", DT_VEL_CG(tmiss)[0]/0.3048);
Message("\n -> Missile Velocity (Y) = %f m/sec", DT_VEL_CG(tmiss)[1]);
Message("\n -> = %f ft/sec", DT_VEL_CG(tmiss)[1]/0.3048);
}
#endif

#if RP_3D
Message("\n -> Missile Velocity (Z) = %f m/sec", DT_VEL_CG(tmiss)[2]);
Message("\n -> = %f ft/sec", DT_VEL_CG(tmiss)[2] / 0.3048);
#endif

V_e = V_avg - Vmiss[0];
Mthrust = V_e * MDOT;

Message("\n -> Relative Velocity = %f m/sec", V_e);
Message("\n -> = %f ft/sec", V_e / 0.3048);
Message("\n");
Message("\n -> Momentum Thrust = %f N", V_e*MDOT);
Message("\n -> = %f lbf", V_e*MDOT / 4.448);
Message("\n");
Message("\n -> Pressure Thrust = %f N", Pthrust);
Message("\n -> = %f lbf", Pthrust / 4.448);
Message("\n");
Message("\n -> TOTAL THRUST = %f N", Pthrust+Mthrust);
Message("\n -> = %f lbf", (Pthrust+Mthrust)/4.448);
Message("\n ****************************************");
Message("\n");
Message("\n");

/* Set calculated thrust as a body force (ejector force) */
prop[SDOF_LOAD_F_X] = Pthrust + Mthrust;
prop[SDOF_LOAD_F_Y] = 0.0;
prop[SDOF_LOAD_F_Z] = 0.0;

/* Dummy Override */
#if RP_2D
prop[SDOF_LOAD_F_Z] = 0.;
if (rp_axi)
prop[SDOF_LOAD_F_Y] = 0.;
#endif

}
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