Searched refs:Sin_alpha (Results 1 – 9 of 9) sorted by relevance
107 CD_clean = -1*CX*Cos_alpha*Cos_beta - CY*Sin_beta - CZ*Sin_alpha*Cos_beta; in add_ice_effects()108 CY_clean = -1*CX*Cos_alpha*Sin_beta + CY*Cos_beta - CZ*Sin_alpha*Sin_beta; in add_ice_effects()109 CL_clean = CX*Sin_alpha - CZ*Cos_alpha; in add_ice_effects()131 CX = -1*CD*Cos_alpha*Cos_beta - CY*Cos_alpha*Sin_beta + CL*Sin_alpha; in add_ice_effects()133 CZ = -1*CD*Sin_alpha*Cos_beta - CY*Sin_alpha*Sin_beta - CL*Cos_alpha; in add_ice_effects()
365 …_X_aero = F_X_wind * Cos_alpha * Cos_beta - F_Y_wind * Cos_alpha * Sin_beta - F_Z_wind * Sin_alpha; in uiuc_force_moment()367 …F_Z_aero = F_X_wind * Sin_alpha * Cos_beta - F_Y_wind * Sin_alpha * Sin_beta + F_Z_wind * Cos_alph… in uiuc_force_moment()
135 p = P_body*Cos_alpha + R_body*Sin_alpha; in cherokee_aero()137 r = -P_body*Sin_alpha + R_body*Cos_alpha; in cherokee_aero()156 Cx = CD - CL*Sin_alpha; in cherokee_aero()165 M_l_aero = (Cl*Cos_alpha - Cn*Sin_alpha)*b*qd*S; in cherokee_aero()167 M_n_aero = (Cl*Sin_alpha + Cn*Cos_alpha)*b*qd*S; in cherokee_aero()
437 dCl_stall = dCl*Cos_alpha - dCn*Sin_alpha; in basic_aero()438 dCn_stall = dCl*Sin_alpha + dCn*Cos_alpha; in basic_aero()451 Cx_drela = -CD_drela*Cos_alpha + CL_drela*Sin_alpha*Cos_beta*Cos_beta; in basic_aero()452 Cz_drela = -CD_drela*Sin_alpha - CL_drela*Cos_alpha*Cos_beta*Cos_beta; in basic_aero()
463 F_X_aero = F_X_wind*Cos_alpha*Cos_beta - F_Y_wind*Cos_alpha*Sin_beta - F_Z_wind*Sin_alpha; in c172_aero()465 F_Z_aero = F_X_wind*Sin_alpha*Cos_beta - F_Y_wind*Sin_alpha*Sin_beta + F_Z_wind*Cos_alpha; in c172_aero()
391 Sin_alpha = sin(Std_Alpha); in ls_aux()
346 #define Sin_alpha generic_.sin_alpha macro
460 SCALAR Cos_alpha, Sin_alpha, Cos_beta; in aero() local463 Sin_alpha = sin(Alpha); in aero()616 dCl_stall = dCl*Cos_alpha - dCn*Sin_alpha; in aero()617 dCn_stall = dCl*Sin_alpha + dCn*Cos_alpha; in aero()634 C_xyz.r[0] = -CD*Cos_alpha + CL*Sin_alpha*Cos_beta*Cos_beta; in aero()635 C_xyz.r[2] = -CD*Sin_alpha - CL*Cos_alpha*Cos_beta*Cos_beta; in aero()
707 double Sin_alpha = sin(Alpha); in aero() local838 dCl_stall = dCl*Cos_alpha - dCn*Sin_alpha; in aero()839 dCn_stall = dCl*Sin_alpha + dCn*Cos_alpha; in aero()854 C_xyz.r[0] = -CD*Cos_alpha + CL*Sin_alpha*Cos_beta*Cos_beta; in aero()855 C_xyz.r[2] = -CD*Sin_alpha - CL*Cos_alpha*Cos_beta*Cos_beta; in aero()