map <string,int> geometry_map;
#define geometry_map aircraft_->geometry_map
- double bw, cbar, Sw, ih, bh, ch, Sh;
+ double bw, cbar, Sw, ih, bh, chord_h, Sh;
#define bw aircraft_->bw
#define cbar aircraft_->cbar
#define Sw aircraft_->Sw
#define ih aircraft_->ih
#define bh aircraft_->bh
-#define ch aircraft_->ch
+#define chord_h aircraft_->chord_h
#define Sh aircraft_->Sh
{
cbar_2U = cbar / (2.0 * V_rel_wind);
b_2U = bw / (2.0 * V_rel_wind);
- // ch is the horizontal tail chord
- ch_2U = ch / (2.0 * V_rel_wind);
+ // chord_h is the horizontal tail chord
+ ch_2U = chord_h / (2.0 * V_rel_wind);
}
else if (use_dyn_on_speed_curve1)
{
V_rel_wind_dum = dyn_on_speed_zero + V_rel_wind * (dyn_on_speed - dyn_on_speed_zero)/dyn_on_speed;
cbar_2U = cbar / (2.0 * V_rel_wind_dum);
b_2U = bw / (2.0 * V_rel_wind_dum);
- ch_2U = ch / (2.0 * V_rel_wind_dum);
+ ch_2U = chord_h / (2.0 * V_rel_wind_dum);
Std_Alpha_dot = 0.0;
}
else
{
cbar_2U = cbar / (2.0 * fabs(U_body));
b_2U = bw / (2.0 * fabs(U_body));
- ch_2U = ch / (2.0 * fabs(U_body));
+ ch_2U = chord_h / (2.0 * fabs(U_body));
}
else if (use_dyn_on_speed_curve1)
{
U_body_dum = dyn_on_speed_zero + fabs(U_body) * (dyn_on_speed - dyn_on_speed_zero)/dyn_on_speed;
cbar_2U = cbar / (2.0 * U_body_dum);
b_2U = bw / (2.0 * U_body_dum);
- ch_2U = ch / (2.0 * U_body_dum);
+ ch_2U = chord_h / (2.0 * U_body_dum);
Std_Alpha_dot = 0.0;
}
else
{
cbar_2U = cbar / (2.0 * U_body);
b_2U = bw / (2.0 * U_body);
- ch_2U = ch / (2.0 * U_body);
+ ch_2U = chord_h / (2.0 * U_body);
}
else if (use_dyn_on_speed_curve1)
{
U_body_dum = dyn_on_speed_zero + U_body * (dyn_on_speed - dyn_on_speed_zero)/dyn_on_speed;
cbar_2U = cbar / (2.0 * U_body_dum);
b_2U = bw / (2.0 * U_body_dum);
- ch_2U = ch / (2.0 * U_body_dum);
+ ch_2U = chord_h / (2.0 * U_body_dum);
Std_Alpha_dot = 0.0;
beta_flow_clean_tail = cbar_2U;
}