Searched refs:eta_tail (Results 1 – 5 of 5) sorted by relevance
78 delta_Cm = (0.75*eta_wing + 0.25*eta_tail)*KCm_alpha + (eta_tail)*KCm_de; in Calc_Iced_Forces()93 delta_Ch = eta_tail*KCh; in Calc_Iced_Forces()
259 eta_tail = uiuc_1Dinterpolation(eta_tail_input_timeArray, in uiuc_coefficients()284 if (eta_tail == 0.2 && tactile_pitch && tactilefadef) in uiuc_coefficients()
1868 fout << eta_tail << " "; in uiuc_recorder()
887 eta_tail = token_value; in parse_ice()
2980 double eta_wing_left, eta_wing_right, eta_tail; member2985 #define eta_tail aircraft_->eta_tail macro