The two unused variables were commented out.
SCALAR Cl_dr;
SCALAR Cn_dr;
- SCALAR CY_da;
+ //SCALAR CY_da;
SCALAR Cl_da;
SCALAR Cn_da;
SCALAR CG_arm;
SCALAR CL_drop;
SCALAR CD_stall = 0.05;
- int stalling;
+ //int stalling;
SCALAR span_eff;
SCALAR CL_CD0;
CY_dr = 0.000000E+00;
Cl_dr = 0.000000E+00;
Cn_dr = 0.000000E+00;
- CY_da = -0.135890;
+ //CY_da = -0.135890;
Cl_da = -0.307921E-02;
Cn_da = 0.527143E-01;
span_eff = 0.95;
dCL_cent = 0.;
dCL_right = 0.;
- stalling=0;
+ //stalling=0;
if (CL_left > CL_max)
{
dCL_left = CL_max-CL_left -CL_drop;
- stalling=1;
+ //stalling=1;
}
if (CL_cent > CL_max)
{
dCL_cent = CL_max-CL_cent -CL_drop;
- stalling=1;
+ //stalling=1;
}
if (CL_right > CL_max)
{
dCL_right = CL_max-CL_right -CL_drop;
- stalling=1;
+ //stalling=1;
}
if (CL_left < CL_min)
{
dCL_left = CL_min-CL_left -CL_drop;
- stalling=1;
+ //stalling=1;
}
if (CL_cent < CL_min)
{
dCL_cent = CL_min-CL_cent -CL_drop;
- stalling=1;
+ //stalling=1;
}
if (CL_right < CL_min)
{
dCL_right = CL_min-CL_right -CL_drop;
- stalling=1;
+ //stalling=1;
}
/* set average wing CL */