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: object

Store extracted aircraft and engine parameters for each aircraft type.

AIRCRAFT INFORMATION#

  • manufacturer Aircraft manufacturer name

  • aircraft_type Specific aircraft type variant

  • n_engine Number of engines

  • winglets Does the aircraft type contain winglets? (True/False)

AIRCRAFT MASS PARAMETERS#

  • amass_mtow Aircraft maximum take-off weight, [\(kg\)]

  • amass_mlw Aircraft maximum landing weight, [\(kg\)]

  • amass_mzfw Aircraft maximum zero fuel weight, [\(kg\)]

  • amass_oew Aircraft operating empty weight, [\(kg\)]

  • amass_mpl Aircraft maximum payload, [\(kg\)]

AIRCRAFT GEOMETRY#

  • wing_surface_area Reference wing surface area, [\(m^{2}\)]

  • wing_span Wing span, [\(m\)]

  • fuselage_width Aircraft fuselage width, [\(m\)]

  • delta_2 Induced drag wing-fuselage interference factor

  • cos_sweep Cosine of wing sweep angle measured at the 1/4 chord line

  • wing_aspect_ratio Wing aspect ratio, wing_span**2 / wing_surface_area

AERODYNAMIC PARAMETERS#

  • psi_0 Aircraft geometry drag parameter

  • x_ref Threshold condition where the terminating shockwave moves onto

    the rear part of the wing

  • wing_constant A constant used in the wave drag model, capturing the aerofoil

    technology factor and wing geometry

  • j_1 Wave drag parameter 1

  • j_2 Wave drag parameter 2

  • j_3 Wave drag parameter 3

  • c_l_do Design optimum lift coefficient

ENGINE PARAMETERS#

  • f_00 Maximum thrust force that can be supplied by the engine at sea level static

    conditions, summed over all engines, [\(N\)].

  • ff_max_sls Fuel mass flow rate at take-off and sea level static conditions, summed

    over all engines, [\(kg s^{-1}\)]

  • ff_idle_sls Fuel mass flow rate under engine idle and sea level static conditions,

    summed over all engines, [\(kg s^{-1}\)]

  • m_des Design optimum Mach number where the fuel mass flow rate is at a minimum.

  • c_t_des Design optimum engine thrust coefficient where the fuel mass flow rate is

    at a minimum.

  • eta_1 Multiplier for maximum overall propulsion efficiency model

  • eta_2 Exponent for maximum overall propulsion efficiency model

  • tr_ec Engine characteristic ratio of total turbine-entry-temperature to

    the total freestream temperature for maximum overall efficiency.

  • m_ec Engine characteristic Mach number associated with tr_ec.

  • tet_mto Turbine entry temperature at maximum take-off rating, [\(K\)]

  • tet_mcc Turbine entry temperature at maximum continuous climb rating, [\(K\)]

HEIGHT AND SPEED LIMITS#

  • fl_max Maximum flight level

  • max_mach_num Maximum operational Mach number

  • p_i_max Maximum operational impact pressure, [\(Pa\)]

  • p_inf_co Crossover 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#