#include "ls_types.h"
#include "ls_generic.h"
#include "ls_cockpit.h"
+#include "ls_constants.h"
-void aero()
+void cherokee_aero()
/*float ** Cherokee (float t, VectorStanja &X, float *U)*/
{
static float
- Cz = Cz0 + Cza*Alpha + Czat*(Alpha_dot*c/2.0/V) + Czq*(q*c/2.0/V) + Czde * elevator;
- Cm = Cm0 + Cma*Alpha + Cmat*(Alpha_dot*c/2.0/V) + Cmq*(q*c/2.0/V) + Cmde * elevator;
+ Cz = Cz0 + Cza*Std_Alpha + Czat*(Std_Alpha_dot*c/2.0/V) + Czq*(q*c/2.0/V) + Czde * elevator;
+ Cm = Cm0 + Cma*Std_Alpha + Cmat*(Std_Alpha_dot*c/2.0/V) + Cmq*(q*c/2.0/V) + Cmde * elevator;
- Cx = Cx0 - (Cza*Alpha)*(Cza*Alpha)/(M_PI*5.71*0.6);
- Cl = Clb*Beta + Clp*(p*b/2.0/V) + Clr*(r*b/2.0/V) + Clda * aileron;
+ Cx = Cx0 - (Cza*Std_Alpha)*(Cza*Std_Alpha)/(LS_PI*5.71*0.6);
+ Cl = Clb*Std_Beta + Clp*(p*b/2.0/V) + Clr*(r*b/2.0/V) + Clda * aileron;
- Cy = Cyb*Beta + Cyr*(r*b/2.0/V);
- Cn = Cnb*Beta + Cnp*(p*b/2.0/V) + Cnr*(r*b/2.0/V) + Cndr * rudder;
+ Cy = Cyb*Std_Beta + Cyr*(r*b/2.0/V);
+ Cn = Cnb*Std_Beta + Cnp*(p*b/2.0/V) + Cnr*(r*b/2.0/V) + Cndr * rudder;
/* back to body axes */
{