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, nominal_opr, nominal_bpr, nominal_fpr, 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, [\(K\)]
nominal_opr Nominal engine operating pressure ratio.
nominal_bpr Nominal engine bypass ratio.
nominal_fpr Nominal engine fan pressure ratio.

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, nominal_opr, nominal_bpr, nominal_fpr, fl_max, max_mach_num, p_i_max, p_inf_co)¶

Methods

__init__(manufacturer, aircraft_type, ...)

Attributes

`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`
`nominal_opr`
`nominal_bpr`
`nominal_fpr`
`fl_max`
`max_mach_num`
`p_i_max`
`p_inf_co`

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¶

nominal_bpr¶

nominal_fpr¶

nominal_opr¶

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¶