pycontrails.models.ps_model.PSAircraftEngineParams#
- class pycontrails.models.ps_model.PSAircraftEngineParams(manufacturer, aircraft_type, n_engine, winglets, amass_mtow, amass_mlw, amass_mzfw, amass_oew, amass_mpl, wing_surface_area, wing_span, fuselage_width, delta_2, cos_sweep, wing_aspect_ratio, psi_0, x_ref, wing_constant, j_1, j_2, j_3, c_l_do, f_00, ff_max_sls, ff_idle_sls, m_des, c_t_des, eta_1, eta_2, tr_ec, m_ec, tet_mto, tet_mcc, fl_max, max_mach_num, p_i_max, p_inf_co)#
Bases:
objectStore extracted aircraft and engine parameters for each aircraft type.
AIRCRAFT INFORMATION#
manufacturerAircraft manufacturer nameaircraft_typeSpecific aircraft type variantn_engineNumber of engineswingletsDoes the aircraft type contain winglets? (True/False)
AIRCRAFT MASS PARAMETERS#
amass_mtowAircraft maximum take-off weight, [\(kg\)]amass_mlwAircraft maximum landing weight, [\(kg\)]amass_mzfwAircraft maximum zero fuel weight, [\(kg\)]amass_oewAircraft operating empty weight, [\(kg\)]amass_mplAircraft maximum payload, [\(kg\)]
AIRCRAFT GEOMETRY#
wing_surface_areaReference wing surface area, [\(m^{2}\)]wing_spanWing span, [\(m\)]fuselage_widthAircraft fuselage width, [\(m\)]delta_2Induced drag wing-fuselage interference factorcos_sweepCosine of wing sweep angle measured at the 1/4 chord linewing_aspect_ratioWing aspect ratio,wing_span**2 / wing_surface_area
AERODYNAMIC PARAMETERS#
psi_0Aircraft geometry drag parameterx_refThreshold condition where the terminating shockwave moves ontothe rear part of the wing
wing_constantA constant used in the wave drag model, capturing the aerofoiltechnology factor and wing geometry
j_1Wave drag parameter 1j_2Wave drag parameter 2j_3Wave drag parameter 3c_l_doDesign optimum lift coefficient
ENGINE PARAMETERS#
f_00Maximum thrust force that can be supplied by the engine at sea level staticconditions, summed over all engines, [\(N\)].
ff_max_slsFuel mass flow rate at take-off and sea level static conditions, summedover all engines, [\(kg s^{-1}\)]
ff_idle_slsFuel mass flow rate under engine idle and sea level static conditions,summed over all engines, [\(kg s^{-1}\)]
m_desDesign optimum Mach number where the fuel mass flow rate is at a minimum.c_t_desDesign optimum engine thrust coefficient where the fuel mass flow rate isat a minimum.
eta_1Multiplier for maximum overall propulsion efficiency modeleta_2Exponent for maximum overall propulsion efficiency modeltr_ecEngine characteristic ratio of total turbine-entry-temperature tothe total freestream temperature for maximum overall efficiency.
m_ecEngine characteristic Mach number associated with tr_ec.tet_mtoTurbine entry temperature at maximum take-off rating, [\(K\)]tet_mccTurbine entry temperature at maximum continuous climb rating, [\(K\)]
HEIGHT AND SPEED LIMITS#
fl_maxMaximum flight levelmax_mach_numMaximum operational Mach numberp_i_maxMaximum operational impact pressure, [\(Pa\)]p_inf_coCrossover pressure altitude, [\(Pa\)]
- __init__(manufacturer, aircraft_type, n_engine, winglets, amass_mtow, amass_mlw, amass_mzfw, amass_oew, amass_mpl, wing_surface_area, wing_span, fuselage_width, delta_2, cos_sweep, wing_aspect_ratio, psi_0, x_ref, wing_constant, j_1, j_2, j_3, c_l_do, f_00, ff_max_sls, ff_idle_sls, m_des, c_t_des, eta_1, eta_2, tr_ec, m_ec, tet_mto, tet_mcc, fl_max, max_mach_num, p_i_max, p_inf_co)#
Methods
__init__(manufacturer, aircraft_type, ...)Attributes
- aircraft_type#
- amass_mlw#
- amass_mpl#
- amass_mtow#
- amass_mzfw#
- amass_oew#
- c_l_do#
- c_t_des#
- cos_sweep#
- delta_2#
- eta_1#
- eta_2#
- f_00#
- ff_idle_sls#
- ff_max_sls#
- fl_max#
- fuselage_width#
- j_1#
- j_2#
- j_3#
- m_des#
- m_ec#
- manufacturer#
- max_mach_num#
- n_engine#
- p_i_max#
- p_inf_co#
- psi_0#
- tet_mcc#
- tet_mto#
- tr_ec#
- wing_aspect_ratio#
- wing_constant#
- wing_span#
- wing_surface_area#
- winglets#
- x_ref#