case simpleSingle_flag:
{
F_X_engine = Throttle[3] * simpleSingleMaxThrust;
+ F_Y_engine = 0.0;
+ F_Z_engine = 0.0;
+ M_l_engine = 0.0;
+ M_m_engine = 0.0;
+ M_n_engine = 0.0;
break;
}
case simpleSingleModel_flag:
/* simple model based on Hepperle's equation
* exponent dtdvvt was computed in uiuc_menu.cpp */
F_X_engine = Throttle[3] * t_v0 * (1 - pow((V_rel_wind/v_t0),dtdvvt));
+ F_Y_engine = 0.0;
+ F_Z_engine = 0.0;
+ M_l_engine = 0.0;
+ M_m_engine = 0.0;
+ M_n_engine = 0.0;
if (b_slipstreamEffects) {
tc = F_X_engine/(Dynamic_pressure * LS_PI * propDia * propDia / 4);
w_induced = 0.5 * V_rel_wind * (-1 + pow((1+tc),.5));
if (eta_q_Cm_q_fac) {eta_q_Cm_q *= eta_q * eta_q_Cm_q_fac;}
if (eta_q_Cm_adot_fac) {eta_q_Cm_adot *= eta_q * eta_q_Cm_adot_fac;}
if (eta_q_Cmfade_fac) {eta_q_Cmfade *= eta_q * eta_q_Cmfade_fac;}
+ if (eta_q_Cm_de_fac) {eta_q_Cm_de *= eta_q * eta_q_Cm_de_fac;}
if (eta_q_Cl_beta_fac) {eta_q_Cl_beta *= eta_q * eta_q_Cl_beta_fac;}
if (eta_q_Cl_p_fac) {eta_q_Cl_p *= eta_q * eta_q_Cl_p_fac;}
if (eta_q_Cl_r_fac) {eta_q_Cl_r *= eta_q * eta_q_Cl_r_fac;}