data:TLAR:NPAX	top-level requirement: number of passengers, assuming a classic eco/business class repartition
data:TLAR:approach_speed	top-level requirement: approach speed
data:TLAR:cruise_mach	top-level requirement: cruise Mach number
data:TLAR:max_TOFL	top-level requirement: maximum takeoff field length
data:TLAR:range	top-level requirement: design range
data:aerodynamics:aircraft:cruise:CD	drag coefficient in cruise conditions w.r.t. data:aerodynamics:aircraft:cruise:CL
data:aerodynamics:aircraft:cruise:CD0	profile drag coefficient for whole aircraft w.r.t. data:aerodynamics:aircraft:cruise:CL
data:aerodynamics:aircraft:cruise:CD:compressibility	increment of drag coefficient due to compressibility effects (shock waves) w.r.t. data:aerodynamics:aircraft:cruise:CL
data:aerodynamics:aircraft:cruise:CD:trim	increment of drag coefficient due to aircraft trim w.r.t. data:aerodynamics:aircraft:cruise:CL
data:aerodynamics:aircraft:cruise:CL	scale of lift coefficient values for drag computations in cruise conditions
data:aerodynamics:aircraft:cruise:CL_alpha	derivative of lift coefficient with respect to angle of attack in cruise conditions
data:aerodynamics:aircraft:cruise:L_D_max	max lift/drag ratio in cruise conditions
data:aerodynamics:aircraft:cruise:induced_drag_coefficient	multiply squared lift coefficient by this coefficient to get induced drag coefficient
data:aerodynamics:aircraft:cruise:optimal_CD	drag coefficient at maximum lift/drag ratio in cruise conditions
data:aerodynamics:aircraft:cruise:optimal_CL	lift coefficient at maximum lift/drag ratio in cruise conditions
data:aerodynamics:aircraft:landing:CL_max	maximum lift coefficient in landing conditions
data:aerodynamics:aircraft:landing:CL_max_clean	maximum lift coefficient in landing conditions without high-lift devices
data:aerodynamics:aircraft:landing:additional_CL_capacity	at landing, is equal to (maximum lift coefficient)-(maximum required lift coefficient)
data:aerodynamics:aircraft:landing:mach	considered Mach number for landing phase
data:aerodynamics:aircraft:low_speed:CD	drag coefficient in low speed conditions (no high-lift) w.r.t. data:aerodynamics:aircraft:low_speed:CL
data:aerodynamics:aircraft:low_speed:CD0	profile drag coefficient for whole aircraft in low speed conditions (no high-lift) w.r.t. data:aerodynamics:aircraft:low_speed:CL
data:aerodynamics:aircraft:low_speed:CD:trim	increment of drag coefficient due to aircraft trim in low speed conditions (no high-lift) w.r.t. data:aerodynamics:aircraft:low_speed:CL
data:aerodynamics:aircraft:low_speed:CL	scale of lift coefficient values for drag computations in low speed conditions
data:aerodynamics:aircraft:low_speed:CL_alpha	derivative of lift coefficient with respect to angle of attack in low speed conditions
data:aerodynamics:aircraft:low_speed:induced_drag_coefficient	multiply squared lift coefficient by this coefficient to get induced drag coefficient
data:aerodynamics:aircraft:takeoff:CL0_clean	value of lift coefficient at angle of attack 0 in clean configuration at takeoff
data:aerodynamics:aircraft:takeoff:CL_alpha	derivative of lift coefficient with respect to angle of attack in takeoff conditions
data:aerodynamics:aircraft:takeoff:mach	considered Mach number for takeoff phase
data:aerodynamics:cruise:neutral_point:x	X-position of neutral point - X-position of aircraft nose
data:aerodynamics:fuselage:cruise:CD0	profile drag coefficient for fuselage w.r.t. data:aerodynamics:aircraft:cruise:CL
data:aerodynamics:fuselage:cruise:CnBeta	derivative of yawing moment against sideslip angle for fuselage in cruise conditions
data:aerodynamics:high_lift_devices:landing:CD	increment of CD due to high-lift devices for landing phase
data:aerodynamics:high_lift_devices:landing:CL	increment of CL due to high-lift devices for landing phase
data:aerodynamics:high_lift_devices:takeoff:CD	increment of CD due to high-lift devices for takeoff phase
data:aerodynamics:high_lift_devices:takeoff:CL	increment of CL due to high-lift devices for takeoff phase
data:aerodynamics:horizontal_tail:cruise:CD0	profile drag coefficient for horizontal tail
data:aerodynamics:horizontal_tail:cruise:CL_alpha	derivative of lift coefficient of horizontal tail with respect to local angle of attack in cruise conditions
data:aerodynamics:nacelles:cruise:CD0	profile drag coefficient for nacelles
data:aerodynamics:pylons:cruise:CD0	profile drag coefficient for pylons
data:aerodynamics:vertical_tail:cruise:CD0	profile drag coefficient for vertical tail
data:aerodynamics:vertical_tail:cruise:CL_alpha	derivative of lift coefficient of horizontal tail with respect to local "angle of attack" in cruise conditions
data:aerodynamics:vertical_tail:cruise:CnBeta	derivative of yawing moment against sideslip angle for vertical tail in cruise conditions
data:aerodynamics:wing:cruise:CD0	profile drag coefficient for wing w.r.t. data:aerodynamics:aircraft:cruise:CL
data:aerodynamics:wing:cruise:reynolds	Reynolds number based on wing mean aerodynamic chord in cruise conditions
data:aerodynamics:wing:low_speed:reynolds	Reynolds number based on wing mean aerodynamic chord in low speed conditions
data:geometry:aircraft:wetted_area	total wetted area
data:geometry:cabin:NPAX1	number of passengers if there are only economical class seats
data:geometry:cabin:aisle_width	width of aisles
data:geometry:cabin:containers:count	total number of cargo containers
data:geometry:cabin:containers:count_by_row	number of cargo containers along width
data:geometry:cabin:crew_count:commercial	number of commercial crew members
data:geometry:cabin:crew_count:technical	number of technical crew members
data:geometry:cabin:exit_width	width of exits
data:geometry:cabin:length	cabin length
data:geometry:cabin:pallet_count	number of pallet in cargo hold
data:geometry:cabin:seat_rows:count	number of seat rows in the cabin
data:geometry:cabin:seats:business:count_by_row	number of business class seats along width
data:geometry:cabin:seats:business:length	length of business class seats
data:geometry:cabin:seats:business:width	width of business class seats
data:geometry:cabin:seats:economical:count_by_row	number of economical class seats along width
data:geometry:cabin:seats:economical:length	length of economical class seats
data:geometry:cabin:seats:economical:width	width of economical class seats
data:geometry:flap:chord_ratio	mean value of (flap chord)/(section chord)
data:geometry:flap:span_ratio	ratio (width of flaps)/(total span)
data:geometry:fuselage:PAX_length	length of passenger-dedicated zone
data:geometry:fuselage:front_length	length of front non-cylindrical part of the fuselage
data:geometry:fuselage:length	total fuselage length
data:geometry:fuselage:maximum_height	maximum fuselage height
data:geometry:fuselage:maximum_width	maximum fuselage width
data:geometry:fuselage:rear_length	length of rear non-cylindrical part of the fuselage
data:geometry:fuselage:wetted_area	wetted area of fuselage
data:geometry:has_T_tail	0=horizontal tail is attached to fuselage / 1=horizontal tail is attached to top of vertical tail
data:geometry:horizontal_tail:MAC:at25percent:x:from_wingMAC25	distance along X between 25% MAC of wing and 25% MAC of horizontal tail
data:geometry:horizontal_tail:MAC:at25percent:x:local	X-position of the 25% of mean aerodynamic chord of horizontal tail w.r.t. leading edge of root chord
data:geometry:horizontal_tail:MAC:length	mean aerodynamic chord length of horizontal tail
data:geometry:horizontal_tail:MAC:y	Y-position of mean aerodynamic chord of horizontal tail
data:geometry:horizontal_tail:area	horizontal tail area
data:geometry:horizontal_tail:aspect_ratio	aspect ratio of horizontal tail
data:geometry:horizontal_tail:root:chord	chord length at root of horizontal tail
data:geometry:horizontal_tail:span	horizontal tail span
data:geometry:horizontal_tail:sweep_0	sweep angle at leading edge of horizontal tail
data:geometry:horizontal_tail:sweep_100	sweep angle at trailing edge of horizontal tail
data:geometry:horizontal_tail:sweep_25	sweep angle at 25% chord of horizontal tail
data:geometry:horizontal_tail:taper_ratio	taper ratio of horizontal tail
data:geometry:horizontal_tail:thickness_ratio	thickness ratio of horizontal tail
data:geometry:horizontal_tail:tip:chord	chord length at tip of horizontal tail
data:geometry:horizontal_tail:volume_coefficient	volume coefficient of horizontal tail
data:geometry:horizontal_tail:wetted_area	wetted area of horizontal tail
data:geometry:landing_gear:front:distance_to_main	distance between front and main landing gears
data:geometry:landing_gear:height	height of landing gear
data:geometry:propulsion:engine:count	number of engines
data:geometry:propulsion:engine:y_ratio	engine position with respect to total span
data:geometry:propulsion:fan:length	engine length
data:geometry:propulsion:layout	position of engines (1=under the wing / 2=rear fuselage)
data:geometry:propulsion:nacelle:diameter	nacelle diameter
data:geometry:propulsion:nacelle:length	nacelle length
data:geometry:propulsion:nacelle:wetted_area	wetted area of nacelle
data:geometry:propulsion:nacelle:y	Y-position of nacelle center
data:geometry:propulsion:pylon:length	pylon length
data:geometry:propulsion:pylon:wetted_area	wetted area of pylon
data:geometry:slat:chord_ratio	mean value of slat chord)/(section chord)
data:geometry:slat:span_ratio	ratio (width of slats)/(total span)
data:geometry:vertical_tail:MAC:at25percent:x:from_wingMAC25	distance along X between 25% MAC of wing and 25% MAC of vertical tail
data:geometry:vertical_tail:MAC:at25percent:x:local	X-position of the 25% of mean aerodynamic chord of vertical tail w.r.t. leading edge of root chord
data:geometry:vertical_tail:MAC:length	mean aerodynamic chord length of vertical tail
data:geometry:vertical_tail:MAC:z	Z-position of mean aerodynamic chord of vertical tail
data:geometry:vertical_tail:area	vertical tail area
data:geometry:vertical_tail:aspect_ratio	aspect ratio of vertical tail
data:geometry:vertical_tail:root:chord	chord length at root of vertical tail
data:geometry:vertical_tail:span	vertical tail span
data:geometry:vertical_tail:sweep_0	sweep angle at leading edge of vertical tail
data:geometry:vertical_tail:sweep_100	sweep angle at trailing edge of vertical tail
data:geometry:vertical_tail:sweep_25	sweep angle at 25% chord of vertical tail
data:geometry:vertical_tail:taper_ratio	taper ratio of vertical tail
data:geometry:vertical_tail:thickness_ratio	thickness ratio of vertical tail
data:geometry:vertical_tail:tip:chord	chord length at tip of vertical tail
data:geometry:vertical_tail:volume_coefficient	volume coefficient of vertical tail
data:geometry:vertical_tail:wetted_area	wetted area of vertical tail
data:geometry:wing:MAC:at25percent:x	X-position of the 25% of mean aerodynamic chord of wing w.r.t. aircraft nose (drives position of wing along fuselage)
data:geometry:wing:MAC:leading_edge:x:local	X-position of leading edge of mean aerodynamic chord w.r.t. leading edge of root chord
data:geometry:wing:MAC:length	length of mean aerodynamic chord of wing
data:geometry:wing:MAC:y	Y-position of mean aerodynamic chord of wing
data:geometry:wing:area	wing reference area
data:geometry:wing:aspect_ratio	wing aspect ratio
data:geometry:wing:b_50	actual length between root and tip along 50% of chord
data:geometry:wing:kink:chord	chord length at wing kink
data:geometry:wing:kink:leading_edge:x:local	X-position of leading edge at wing kink w.r.t. leading edge of root chord
data:geometry:wing:kink:span_ratio	ratio (Y-position of kink)/(semi-span)
data:geometry:wing:kink:thickness_ratio	thickness ratio at wing kink
data:geometry:wing:kink:y	Y-position of wing kink
data:geometry:wing:outer_area	wing area outside of fuselage
data:geometry:wing:root:chord	chord length at wing root
data:geometry:wing:root:thickness_ratio	thickness ratio at wing root
data:geometry:wing:root:virtual_chord	virtual chord length at wing root if sweep angle of trailing edge of outer wing part was on the whole wing (no kink)
data:geometry:wing:root:y	Y-position of wing root
data:geometry:wing:span	wing span
data:geometry:wing:spar_ratio:front:kink	ratio (front spar position)/(chord length) at wing kink
data:geometry:wing:spar_ratio:front:root	ratio (front spar position)/(chord length) at wing root
data:geometry:wing:spar_ratio:front:tip	ratio (front spar position)/(chord length) at wing tip
data:geometry:wing:spar_ratio:rear:kink	ratio (rear spar position)/(chord length) at wing kink
data:geometry:wing:spar_ratio:rear:root	ratio (rear spar position)/(chord length) at wing root
data:geometry:wing:spar_ratio:rear:tip	ratio (rear spar position)/(chord length) at wing tip
data:geometry:wing:sweep_0	sweep angle at leading edge of wing
data:geometry:wing:sweep_100_inner	sweep angle at trailing edge of wing (inner side of the kink)
data:geometry:wing:sweep_100_outer	sweep angle at trailing edge of wing (outer side of the kink)
data:geometry:wing:sweep_25	sweep angle at 25% chord of wing
data:geometry:wing:taper_ratio	taper ratio of wing
data:geometry:wing:thickness_ratio	mean thickness ratio of wing
data:geometry:wing:tip:chord	chord length at wing tip
data:geometry:wing:tip:leading_edge:x:local	X-position of leading edge at wing tip w.r.t. leading edge of root chord
data:geometry:wing:tip:thickness_ratio	thickness ratio at wing tip
data:geometry:wing:tip:y	Y-position of wing tip
data:geometry:wing:wetted_area	wetted area of wing
data:handling_qualities:static_margin	(X-position of neutral point - X-position of center of gravity ) / (mean aerodynamic chord)
data:load_case:lc1:U_gust	gust vertical speed for sizing load case 1 (gust with minimum aircraft mass)
data:load_case:lc1:Vc_EAS	equivalent air speed for sizing load case 1 (gust with minimum aircraft mass)
data:load_case:lc1:altitude	altitude for sizing load case 1 (gust with minimum aircraft mass)
data:load_case:lc2:U_gust	gust vertical speed for sizing load case 2 (gust with maximum aircraft mass)
data:load_case:lc2:Vc_EAS	equivalent air speed for sizing load case 2 (gust with maximum aircraft mass)
data:load_case:lc2:altitude	altitude for sizing load case 2 (gust with maximum aircraft mass)
data:mission:operational:climb:thrust_rate	thrust rate (between 0.0 and 1.0) during climb phase in operational mission
data:mission:operational:descent:thrust_rate	thrust rate (between 0.0 and 1.0) during descent phase in operational mission
data:mission:operational:diversion:climb:duration	duration of diversion climb phase in operational mission
data:mission:operational:diversion:climb:fuel	mass of consumed fuel during diversion climb phase in operational mission
data:mission:operational:diversion:cruise:distance	travelled distance during diversion cruise phase in operational mission
data:mission:operational:diversion:cruise:duration	duration of diversion cruise phase in operational mission
data:mission:operational:diversion:cruise:fuel	mass of consumed fuel during diversion cruise phase in operational mission
data:mission:operational:diversion:descent:duration	duration of diversion descent phase in operational mission
data:mission:operational:diversion:descent:fuel	mass of consumed fuel during diversion descent phase in operational mission
data:mission:operational:flight:duration	total flight time in operational mission
data:mission:operational:flight:fuel	mass of total fuel consumed during flight in operational mission
data:mission:operational:flight:range	total travelled distance during flight in operational mission
data:mission:operational:holding:CAS	Calibrated Air Speed during holding phase in operational mission
data:mission:operational:holding:altitude	altitude during holding phase in operational mission
data:mission:operational:holding:duration	duration of holding phase in operational mission
data:mission:operational:holding:fuel	mass of consumed fuel during holding phase in operational mission
data:mission:operational:initial_climb:fuel	mass of consumed fuel during initial climb phase in operational mission
data:mission:operational:landing:duration	duration of landing phase in operational mission
data:mission:operational:landing:flap_angle	flap angle during landing phase in operational mission
data:mission:operational:landing:friction_coefficient_brake	ground friction coefficient with full brakes in operational mission
data:mission:operational:landing:fuel	mass of consumed fuel during landing phase in operational mission
data:mission:operational:landing:length	runway length required for landing in operational mission
data:mission:operational:landing:slat_angle	slat angle during landing phase in operational mission
data:mission:operational:landing:thrust_rate	thrust rate (between 0.0 and 1.0) during landing phase in operational mission
data:mission:operational:main_route:climb:duration	duration of climb phase in operational mission
data:mission:operational:main_route:climb:fuel	mass of consumed fuel during climb phase in operational mission
data:mission:operational:main_route:climb:max_climb_rate	maximum climb rate in operational mission
data:mission:operational:main_route:cruise:altitude	altitude during cruise phase in operational mission
data:mission:operational:main_route:cruise:duration	duration of cruise phase in operational mission
data:mission:operational:main_route:cruise:fuel	mass of consumed fuel during cruise phase in operational mission
data:mission:operational:main_route:cruise:mach	Mach number during cruise phase in operational mission
data:mission:operational:main_route:descent:duration	duration of descent phase in operational mission
data:mission:operational:main_route:descent:fuel	mass of consumed fuel during descent phase in operational mission
data:mission:operational:takeoff:TOFL	TakeOff Field Length in operational mission
data:mission:operational:takeoff:V2	safety speed before reaching 35 feet height in operational mission
data:mission:operational:takeoff:VLOF	lift-off speed in operational mission
data:mission:operational:takeoff:VMCA	air minimum control speed in operational mission
data:mission:operational:takeoff:VR	rotation speed in operational mission
data:mission:operational:takeoff:altitude	altitude at takeoff in operational mission
data:mission:operational:takeoff:delta_ISA	ISA temperature increment during takeoff phase in operational mission
data:mission:operational:takeoff:duration	duration of takeoff phase in operational mission
data:mission:operational:takeoff:flap_angle	flap angle during takeoff phase in operational mission
data:mission:operational:takeoff:friction_coefficient_no_brake	ground friction coefficient with no brake in operational mission
data:mission:operational:takeoff:fuel	mass of consumed fuel during takeoff phase in operational mission
data:mission:operational:takeoff:slat_angle	slat angle during takeoff phase in operational mission
data:mission:operational:taxi_in:duration	duration of taxi-in phase in operational mission
data:mission:operational:taxi_in:fuel	mass of consumed fuel during taxi-in phase in operational mission
data:mission:operational:taxi_in:speed	speed during taxi-in phase in operational mission
data:mission:operational:taxi_in:thrust_rate	thrust rate (between 0.0 and 1.0) during taxi-in phase in operational mission
data:mission:operational:taxi_out:duration	duration of taxi-out phase in operational mission
data:mission:operational:taxi_out:fuel	mass of consumed fuel during taxi-out phase in operational mission
data:mission:operational:taxi_out:speed	speed during taxi-out phase in operational mission
data:mission:operational:taxi_out:thrust_rate	thrust rate (between 0.0 and 1.0) during taxi-out phase in operational mission
data:mission:sizing:ZFW	aircraft mass with payload, without fuel, in sizing mission
data:mission:sizing:block_fuel	total fuel mass at start
data:mission:sizing:block_time	total duration of mission
data:mission:sizing:climb:thrust_rate	thrust rate (between 0.0 and 1.0) during climb phase in sizing mission
data:mission:sizing:cs25:sizing_load_1	sizing load during gust with minimum aircraft mass
data:mission:sizing:cs25:sizing_load_2	sizing load during gust with maximum aircraft mass
data:mission:sizing:descent:thrust_rate	thrust rate (between 0.0 and 1.0) during descent phase in sizing mission
data:mission:sizing:diversion:climb:duration	duration of diversion climb phase in sizing mission
data:mission:sizing:diversion:climb:fuel	mass of consumed fuel during diversion climb phase in sizing mission
data:mission:sizing:diversion:cruise:distance	travelled distance during diversion cruise phase in sizing mission
data:mission:sizing:diversion:cruise:duration	duration of diversion cruise phase in sizing mission
data:mission:sizing:diversion:cruise:fuel	mass of consumed fuel during diversion cruise phase in sizing mission
data:mission:sizing:diversion:descent:duration	duration of diversion descent phase in sizing mission
data:mission:sizing:diversion:descent:fuel	mass of consumed fuel during diversion descent phase in sizing mission
data:mission:sizing:diversion:distance	distance to travel during diversion in sizing mission
data:mission:sizing:flight:duration	total flight time in sizing mission
data:mission:sizing:flight:fuel	mass of consumed fuel during flight in sizing mission
data:mission:sizing:fuel	consumed fuel mass during whole mission
data:mission:sizing:fuel:unitary	consumption/passenger/distance_unit in sizing mission
data:mission:sizing:fuel_reserve	mass of fuel reserve
data:mission:sizing:holding:CAS	Calibrated Air Speed during holding phase in sizing mission
data:mission:sizing:holding:altitude	altitude during holding phase in sizing mission
data:mission:sizing:holding:duration	duration of holding phase in sizing mission
data:mission:sizing:holding:fuel	mass of consumed fuel during holding phase in sizing mission
data:mission:sizing:initial_climb:fuel	mass of consumed fuel during initial climb phase in sizing mission
data:mission:sizing:landing:duration	duration of landing phase in sizing mission
data:mission:sizing:landing:flap_angle	flap angle during landing phase in sizing mission
data:mission:sizing:landing:friction_coefficient_brake	ground friction coefficient with full brakes in sizing mission
data:mission:sizing:landing:fuel	mass of consumed fuel during landing phase in sizing mission
data:mission:sizing:landing:length	runway length required for landing in sizing mission
data:mission:sizing:landing:slat_angle	slat angle during landing phase in sizing mission
data:mission:sizing:landing:thrust_rate	thrust rate (between 0.0 and 1.0) during landing phase in sizing mission
data:mission:sizing:main_route:climb:distance	covered ground distance during climb phase
data:mission:sizing:main_route:climb:duration	duration of climb phase in sizing mission
data:mission:sizing:main_route:climb:fuel	mass of consumed fuel during climb phase in sizing mission
data:mission:sizing:main_route:climb:max_climb_rate	maximum climb rate in sizing mission
data:mission:sizing:main_route:cruise:altitude	altitude during cruise phase in sizing mission
data:mission:sizing:main_route:cruise:distance	covered ground distance during cruise phase
data:mission:sizing:main_route:cruise:duration	duration of cruise phase in sizing mission
data:mission:sizing:main_route:cruise:fuel	mass of consumed fuel during cruise phase in sizing mission
data:mission:sizing:main_route:cruise:mass_ratio	ratio (aircraft mass at end of cruise)/(aircraft mass at start of cruise)
data:mission:sizing:main_route:descent:distance	covered ground distance during descent phase
data:mission:sizing:main_route:descent:duration	duration of descent phase in sizing mission
data:mission:sizing:main_route:descent:fuel	mass of consumed fuel during descent phase in sizing mission
data:mission:sizing:main_route:fuel	mass of total fuel consumed during flight in sizing mission
data:mission:sizing:takeoff:TOFL	TakeOff Field Length in sizing mission
data:mission:sizing:takeoff:V2	safety speed before reaching 35 feet height in sizing mission
data:mission:sizing:takeoff:VLOF	lift-off speed in sizing mission
data:mission:sizing:takeoff:VMCA	air minimum control speed in sizing mission
data:mission:sizing:takeoff:VR	rotation speed in sizing mission
data:mission:sizing:takeoff:altitude	altitude at takeoff in sizing mission
data:mission:sizing:takeoff:delta_ISA	ISA temperature increment during takeoff phase in sizing mission
data:mission:sizing:takeoff:duration	duration of takeoff phase in sizing mission
data:mission:sizing:takeoff:flap_angle	flap angle during takeoff phase in sizing mission
data:mission:sizing:takeoff:friction_coefficient_no_brake	ground friction coefficient with no brake in sizing mission
data:mission:sizing:takeoff:fuel	mass of consumed fuel during takeoff phase in sizing mission
data:mission:sizing:takeoff:slat_angle	slat angle during takeoff phase in sizing mission
data:mission:sizing:taxi_in:duration	duration of taxi-in phase in sizing mission
data:mission:sizing:taxi_in:fuel	mass of consumed fuel during taxi-in phase in sizing mission
data:mission:sizing:taxi_in:speed	speed during taxi-in phase in sizing mission
data:mission:sizing:taxi_in:thrust_rate	thrust rate (between 0.0 and 1.0) during taxi-in phase in sizing mission
data:mission:sizing:taxi_out:duration	duration of taxi-out phase in sizing mission
data:mission:sizing:taxi_out:fuel	mass of consumed fuel during taxi-out phase in sizing mission
data:mission:sizing:taxi_out:speed	speed during taxi-out phase in sizing mission
data:mission:sizing:taxi_out:thrust_rate	thrust rate (between 0.0 and 1.0) during taxi-out phase in sizing mission
data:propulsion:MTO_thrust	maximum thrust of one engine at sea level
data:propulsion:SFC	Specific Fuel Consumption (can be a vector)
data:propulsion:altitude	altitude for propulsion calculation (can be a vector)
data:propulsion:mach	Mach number for propulsion calculation (can be a vector)
data:propulsion:phase	flight phase for propulsion calculation (can be a vector): TafeOff=1 / Climb=2 / Cruise=3 / Idle=4
data:propulsion:required_thrust	thrust setpoint (can be a vector). Used if "data:propulsion:use_thrust_rate" is 0
data:propulsion:required_thrust_rate	thrust setpoint (can be a vector). Used if "data:propulsion:use_thrust_rate" is 1
data:propulsion:rubber_engine:bypass_ratio	bypass ratio for rubber engine model
data:propulsion:rubber_engine:delta_t4_climb	As it is a delta, unit is K or °C, but is not specified to avoid OpenMDAO making unwanted conversion
data:propulsion:rubber_engine:delta_t4_cruise	As it is a delta, unit is K or °C, but is not specified to avoid OpenMDAO making unwanted conversion
data:propulsion:rubber_engine:design_altitude	design altitude for rubber engine model
data:propulsion:rubber_engine:maximum_mach	maximum Mach number for rubber engine model
data:propulsion:rubber_engine:overall_pressure_ratio	Overall pressure ratio for rubber engine model
data:propulsion:rubber_engine:turbine_inlet_temperature	design turbine inlet temperature (T4) for rubber engine model
data:propulsion:thrust	actual thrust value (can be a vector)
data:propulsion:thrust_rate	actual thrust rate (can be a vector)
data:propulsion:use_thrust_rate	(can be a vector) If 1, calculation will use data:propulsion:required_thrust_rate. If 0, calculation will use data:propulsion:required_thrust
data:weight:aircraft:CG:aft:MAC_position	most aft X-position of center of gravity as ratio of mean aerodynamic chord
data:weight:aircraft:CG:aft:x	most aft X-position of aircraft center of gravity
data:weight:aircraft:LW	landing weight
data:weight:aircraft:MFW	maximum fuel weight
data:weight:aircraft:MLW	maximum landing weight
data:weight:aircraft:MTOW	maximum takeoff weight
data:weight:aircraft:MZFW	maximum zero fuel weight
data:weight:aircraft:OWE	operating weight - empty
data:weight:aircraft:additional_fuel_capacity	fuel mass capacity of wing that exceeds sizing mission requirement
data:weight:aircraft:empty:CG:MAC_position	X-position of center of gravity as ratio of mean aerodynamic chord for empty aircraft
data:weight:aircraft:load_case_1:CG:MAC_position	X-position of center of gravity as ratio of mean aerodynamic chord for load case 1
data:weight:aircraft:load_case_2:CG:MAC_position	X-position of center of gravity as ratio of mean aerodynamic chord for load case 2
data:weight:aircraft:load_case_3:CG:MAC_position	X-position of center of gravity as ratio of mean aerodynamic chord for load case 3
data:weight:aircraft:load_case_4:CG:MAC_position	X-position of center of gravity as ratio of mean aerodynamic chord for load case 4
data:weight:aircraft:max_payload	max payload weight
data:weight:aircraft:payload	design payload weight
data:weight:aircraft_empty:CG:x	X-position center of gravity of empty aircraft
data:weight:aircraft_empty:mass	mass of empty aircraft (=OWE - mass of crew)
data:weight:airframe:CG:x	airframe (A): X-position of center of gravity
data:weight:airframe:flight_controls:CG:x	flight controls (A4): X-position of center of gravity
data:weight:airframe:flight_controls:mass	flight controls (A4): total mass
data:weight:airframe:fuselage:CG:x	fuselage (A2): X-position of center of gravity
data:weight:airframe:fuselage:mass	fuselage (A2): total mass
data:weight:airframe:horizontal_tail:CG:x	horizontal tail (A31): X-position of center of gravity
data:weight:airframe:horizontal_tail:mass	horizontal tail (A31): mass
data:weight:airframe:landing_gear:front:CG:x	front landing gear (A52): X-position of center of gravity
data:weight:airframe:landing_gear:front:mass	front landing gear (A52): mass
data:weight:airframe:landing_gear:main:CG:x	main landing gear (A51): X-position of center of gravity
data:weight:airframe:landing_gear:main:mass	main landing gear (A51): mass
data:weight:airframe:mass	airframe (A): mass
data:weight:airframe:paint:CG:x	paint (A7): X-position of center of gravity
data:weight:airframe:paint:mass	paint (A7): total mass
data:weight:airframe:pylon:CG:x	pylon (A6): X-position of center of gravity
data:weight:airframe:pylon:mass	pylon (A6): total mass
data:weight:airframe:vertical_tail:CG:x	vertical tail (A32): X-position of center of gravity
data:weight:airframe:vertical_tail:mass	vertical tail (A32): mass
data:weight:airframe:wing:CG:x	wing (A1): X-position of center of gravity
data:weight:airframe:wing:mass	wing (A1): total mass
data:weight:crew:CG:x	crew (E): X-position of center of gravity
data:weight:crew:mass	crew (E): mass
data:weight:fuel_tank:CG:x	fuel tank: X-position of center of gravity
data:weight:furniture:CG:x	aircraft furniture (D): X-position of center of gravity
data:weight:furniture:cargo_configuration:CG:x	cargo configuration (D1): X-position of center of gravity
data:weight:furniture:cargo_configuration:mass	cargo configuration (D1): mass
data:weight:furniture:food_water:CG:x	food water (D3): X-position of center of gravity
data:weight:furniture:food_water:mass	food water (D3): mass
data:weight:furniture:mass	aircraft furniture (D): mass
data:weight:furniture:passenger_seats:CG:x	passenger seats (D2): X-position of center of gravity
data:weight:furniture:passenger_seats:mass	passenger seats (D2): mass
data:weight:furniture:security_kit:CG:x	security kit (D4): X-position of center of gravity
data:weight:furniture:security_kit:mass	security kit (D4): mass
data:weight:furniture:toilets:CG:x	toilets (D5): X-position of center of gravity
data:weight:furniture:toilets:mass	toilets (D5): mass
data:weight:payload:PAX:CG:x	passengers: X-position of center of gravity
data:weight:payload:front_fret:CG:x	front fret: X-position of center of gravity
data:weight:payload:rear_fret:CG:x	rear fret: X-position of center of gravity
data:weight:propulsion:CG:x	propulsion system (B): X-position of center of gravity
data:weight:propulsion:engine:CG:x	engine (B1): X-position of center of gravity
data:weight:propulsion:engine:mass	engine (B1): mass
data:weight:propulsion:fuel_lines:CG:x	fuel lines (B2): X-position of center of gravity
data:weight:propulsion:fuel_lines:mass	fuel lines (B2): mass
data:weight:propulsion:mass	propulsion system (B): mass
data:weight:propulsion:unconsumables:CG:x	unconsumables (B3): X-position of center of gravity
data:weight:propulsion:unconsumables:mass	unconsumables (B3): mass
data:weight:systems:CG:x	aircraft systems (C): X-position of center of gravity
data:weight:systems:flight_kit:CG:x	flight kit (C6): X-position of center of gravity
data:weight:systems:flight_kit:mass	flight kit (C6): mass
data:weight:systems:life_support:air_conditioning:CG:x	air conditioning (C2): X-position of center of gravity
data:weight:systems:life_support:air_conditioning:mass	air conditioning (C2): mass
data:weight:systems:life_support:cabin_lighting:CG:x	cabin lighting (C2): X-position of center of gravity
data:weight:systems:life_support:cabin_lighting:mass	cabin lighting (C2): mass
data:weight:systems:life_support:de-icing:CG:x	de-icing (C2): X-position of center of gravity
data:weight:systems:life_support:de-icing:mass	de-icing (C2): mass
data:weight:systems:life_support:insulation:CG:x	insulation (C21): X-position of center of gravity
data:weight:systems:life_support:insulation:mass	insulation (C21): mass
data:weight:systems:life_support:oxygen:CG:x	oxygen (C21): X-position of center of gravity
data:weight:systems:life_support:oxygen:mass	oxygen (C21): mass
data:weight:systems:life_support:safety_equipment:CG:x	safety equipment (C21): X-position of center of gravity
data:weight:systems:life_support:safety_equipment:mass	safety equipment (C21): mass
data:weight:systems:life_support:seats_crew_accommodation:CG:x	seats crew accommodation (C21): X-position of center of gravity
data:weight:systems:life_support:seats_crew_accommodation:mass	seats crew accommodation (C21): mass
data:weight:systems:mass	aircraft systems (C): mass
data:weight:systems:navigation:CG:x	navigation (C3): X-position of center of gravity
data:weight:systems:navigation:mass	navigation (C3): mass
data:weight:systems:operational:cargo_hold:CG:x	cargo hold (C52): X-position of center of gravity
data:weight:systems:operational:cargo_hold:mass	cargo hold (C52): mass
data:weight:systems:operational:radar:CG:x	radar (C51): X-position of center of gravity
data:weight:systems:operational:radar:mass	radar (C51): mass
data:weight:systems:power:auxiliary_power_unit:CG:x	power (C1): X-position of center of gravity
data:weight:systems:power:auxiliary_power_unit:mass	power (C1): mass
data:weight:systems:power:electric_systems:CG:x	power (C1): X-position of center of gravity
data:weight:systems:power:electric_systems:mass	power (C1): mass
data:weight:systems:power:hydraulic_systems:CG:x	power (C1): X-position of center of gravity
data:weight:systems:power:hydraulic_systems:mass	power (C1): mass
data:weight:systems:transmission:CG:x	transmission (C4): X-position of center of gravity
data:weight:systems:transmission:mass	transmission (C4): mass
settings:mission:sizing:breguet:climb:mass_ratio	For Breguet performance computation: assumption of (mass at end of climb) / (mass at start of climb)
settings:mission:sizing:breguet:climb_descent_distance	For Breguet performance computation: assumption of ground distance covered during climb + descent
settings:mission:sizing:breguet:descent:mass_ratio	For Breguet performance computation: assumption of (mass at end of descent) / (mass at start of descent)
settings:mission:sizing:breguet:reserve:mass_ratio	For Breguet performance computation: (weight of fuel reserve)/ZFW
settings:weight:aircraft:CG:range	distance between front position and aft position of CG, as ratio of mean aerodynamic chord (allows to have front position of CG, as currently, FAST-OAD estimates only the aft position of CG)
settings:weight:airframe:flight_controls:mass:k_fc	flight controls (A4): 0.85e-4 if electrical, 1.35e-4 if conventional
settings:weight:airframe:fuselage:mass:k_fus	correction coefficient: 1.00 if all engines under wing / 1.02 with 2 engines at rear / 1.03 if 3 engines at rear / 1.05 if 1 engine in vertical tail (with or without 2 engines under wing)
settings:weight:airframe:fuselage:mass:k_lg	correction coefficient: 1.05 if main landing gear under wing / 1.10 if main landing gear under fuselage
settings:weight:airframe:landing_gear:front:weight_ratio	part of aircraft weight that is supported by front landing gear
settings:weight:airframe:wing:mass:k_mvo	1.39 for Airbus type aircrafts
settings:weight:airframe:wing:mass:k_voil	1.00 if 4 engines / 1.05 if 2 or 3 engines / 1.10 if engines on fuselage
settings:weight:systems:power:mass:k_elec	electricity coefficient: 1.00 if 2 engines (A300, A310 type) / (1.02 if 2 engines (DC9, Caravelle type) / 1.03 if 3 engines (B727 type) / 1.05 if 3 engines (DC10, L1011 type) / 1.08 if 4 engines (B747 type)
test:test_variable	for testing (do not remove, keep first)
tuning:aerodynamics:aircraft:cruise:CD:compressibility:ceiling	maximum authorized value for compressibility drag. Allows to prevent the model from overestimating the compressibility effect, especially for aircraft models after year 2000.
tuning:aerodynamics:aircraft:cruise:CD:k	correction ratio to apply to computed drag coefficient in cruise conditions
tuning:aerodynamics:aircraft:cruise:CD:offset	correction offset to apply to computed drag coefficient in cruise conditions
tuning:aerodynamics:aircraft:cruise:CD:winglet_effect:k	correction ratio to apply to computed induced drag coefficient in cruise conditions
tuning:aerodynamics:aircraft:cruise:CD:winglet_effect:offset	correction ratio to apply to computed drag coefficient in cruise conditions
tuning:aerodynamics:aircraft:cruise:CL:k	ratio to apply to defined cl range (which goes by default from 0.0 to 1.5) in cruise polar computation
tuning:aerodynamics:aircraft:cruise:CL:offset	offset to apply to defined cl range (which goes by default from 0.0 to 1.5) in cruise polar computation
tuning:aerodynamics:aircraft:cruise:CL:winglet_effect:k	ratio to apply to defined cl range (which goes by default from 0.0 to 1.5) in cruise polar computation
tuning:aerodynamics:aircraft:cruise:CL:winglet_effect:offset	offset to apply to defined cl range (which goes by default from 0.0 to 1.5) in cruise polar computation
tuning:aerodynamics:aircraft:landing:CL_max:landing_gear_effect:k	correction ratio to apply to computed maximum lift coefficient in landing conditions to take into account effect of landing gear
tuning:aerodynamics:aircraft:landing:CL_max:landing_gear_effect:offset	correction offset to apply to computed maximum lift coefficient in landing conditions to take into account effect of landing gear
tuning:weight:airframe:flight_controls:mass:k	flight controls (A4): correction ratio to be applied on computed mass
tuning:weight:airframe:flight_controls:mass:offset	flight controls (A4): correction offset to be applied on computed mass
tuning:weight:airframe:fuselage:mass:k	fuselage (A2): correction ratio to be applied on computed mass
tuning:weight:airframe:fuselage:mass:offset	fuselage (A2): correction offset to be applied on computed mass
tuning:weight:airframe:horizontal_tail:mass:k	horizontal tail (A31): correction ratio to be applied on computed mass
tuning:weight:airframe:horizontal_tail:mass:offset	horizontal tail (A31): correction offset to be applied on computed mass
tuning:weight:airframe:landing_gear:mass:k	landing gears (A5): correction ratio to be applied on computed mass
tuning:weight:airframe:landing_gear:mass:offset	landing gears (A5): correction offset to be applied on computed mass
tuning:weight:airframe:paint:mass:k	paint (A7): correction ratio to be applied on computed mass
tuning:weight:airframe:paint:mass:offset	paint (A7): correction offset to be applied on computed mass
tuning:weight:airframe:pylon:mass:k	pylon (A6): correction ratio to be applied on computed mass
tuning:weight:airframe:pylon:mass:offset	pylon (A6): correction offset to be applied on computed mass
tuning:weight:airframe:vertical_tail:mass:k	vertical tail (A32): correction ratio to be applied on computed mass
tuning:weight:airframe:vertical_tail:mass:offset	vertical tail (A32): correction offset to be applied on computed mass
tuning:weight:airframe:wing:bending_sizing:mass:k	wing bending sizing (A11): correction ratio to be applied on computed mass
tuning:weight:airframe:wing:bending_sizing:mass:offset	wing bending sizing (A11): correction offset to be applied on computed mass
tuning:weight:airframe:wing:mass:k	wing (A1): correction ratio to be applied on computed mass
tuning:weight:airframe:wing:mass:offset	wing (A1): correction offset to be applied on computed mass
tuning:weight:airframe:wing:reinforcements:mass:k	wing reinforcements (A14): correction ratio to be applied on computed mass
tuning:weight:airframe:wing:reinforcements:mass:offset	wing reinforcements (A14): correction offset to be applied on computed mass
tuning:weight:airframe:wing:ribs:mass:k	wing ribs (A13): correction ratio to be applied on computed mass
tuning:weight:airframe:wing:ribs:mass:offset	wing ribs (A13): correction offset to be applied on computed mass
tuning:weight:airframe:wing:secondary_parts:mass:k	wing secondary parts (A15): correction ratio to be applied on computed mass
tuning:weight:airframe:wing:secondary_parts:mass:offset	wing secondary parts (A15): correction offset to be applied on computed mass
tuning:weight:airframe:wing:shear_sizing:mass:k	wing shear sizing (A12): correction ratio to be applied on computed mass
tuning:weight:airframe:wing:shear_sizing:mass:offset	wing shear sizing (A12): correction offset to be applied on computed mass
tuning:weight:furniture:cargo_configuration:mass:k	cargo configuration (D1): correction ratio to be applied on computed mass
tuning:weight:furniture:cargo_configuration:mass:offset	cargo configuration (D1): correction offset to be applied on computed mass
tuning:weight:furniture:food_water:mass:k	food water (D3): correction ratio to be applied on computed mass
tuning:weight:furniture:food_water:mass:offset	food water (D3): correction offset to be applied on computed mass
tuning:weight:furniture:passenger_seats:mass:k	passenger seats (D2): correction ratio to be applied on computed mass
tuning:weight:furniture:passenger_seats:mass:offset	passenger seats (D2): correction offset to be applied on computed mass
tuning:weight:furniture:security_kit:mass:k	security kit (D4): correction ratio to be applied on computed mass
tuning:weight:furniture:security_kit:mass:offset	security kit (D4): correction offset to be applied on computed mass
tuning:weight:furniture:toilets:mass:k	toilets (D5): correction ratio to be applied on computed mass
tuning:weight:furniture:toilets:mass:offset	toilets (D5): correction offset to be applied on computed mass
tuning:weight:propulsion:engine:mass:k	engine (B1): correction ratio to be applied on computed mass
tuning:weight:propulsion:engine:mass:offset	engine (B1): correction offset to be applied on computed mass
tuning:weight:propulsion:fuel_lines:mass:k	fuel lines (B2): correction ratio to be applied on computed mass
tuning:weight:propulsion:fuel_lines:mass:offset	fuel lines (B2): correction offset to be applied on computed mass
tuning:weight:propulsion:unconsumables:mass:k	unconsumables (B3): correction ratio to be applied on computed mass
tuning:weight:propulsion:unconsumables:mass:offset	unconsumables (B3): correction offset to be applied on computed mass
tuning:weight:systems:flight_kit:mass:k	flight kit (C6): correction ratio to be applied on computed mass
tuning:weight:systems:flight_kit:mass:offset	flight kit (C6): correction offset to be applied on computed mass
tuning:weight:systems:life_support:air_conditioning:mass:k	air conditioning (C21): correction ratio to be applied on computed mass
tuning:weight:systems:life_support:air_conditioning:mass:offset	air conditioning (C21): correction offset to be applied on computed mass
tuning:weight:systems:life_support:cabin_lighting:mass:k	cabin lighting (C21): correction ratio to be applied on computed mass
tuning:weight:systems:life_support:cabin_lighting:mass:offset	cabin lighting (C21): correction offset to be applied on computed mass
tuning:weight:systems:life_support:de-icing:mass:k	de-icing (C21): correction ratio to be applied on computed mass
tuning:weight:systems:life_support:de-icing:mass:offset	de-icing (C21): correction offset to be applied on computed mass
tuning:weight:systems:life_support:insulation:mass:k	insulation (C21): correction ratio to be applied on computed mass
tuning:weight:systems:life_support:insulation:mass:offset	insulation (C21): correction offset to be applied on computed mass
tuning:weight:systems:life_support:oxygen:mass:k	oxygen (C21): correction ratio to be applied on computed mass
tuning:weight:systems:life_support:oxygen:mass:offset	oxygen (C21): correction offset to be applied on computed mass
tuning:weight:systems:life_support:safety_equipment:mass:k	safety equipment (C21): correction ratio to be applied on computed mass
tuning:weight:systems:life_support:safety_equipment:mass:offset	safety equipment (C21): correction offset to be applied on computed mass
tuning:weight:systems:life_support:seats_crew_accommodation:mass:k	seats crew accommodation (C21): correction ratio to be applied on computed mass
tuning:weight:systems:life_support:seats_crew_accommodation:mass:offset	seats crew accommodation (C21): correction offset to be applied on computed mass
tuning:weight:systems:navigation:mass:k	navigation (C3): correction ratio to be applied on computed mass
tuning:weight:systems:navigation:mass:offset	navigation (C3): correction offset to be applied on computed mass
tuning:weight:systems:operational:mass:k	operational (C5): correction ratio to be applied on computed mass
tuning:weight:systems:operational:mass:offset	operational (C5): correction offset to be applied on computed mass
tuning:weight:systems:power:auxiliary_power_unit:mass:k	power (C1): correction ratio to be applied on computed mass
tuning:weight:systems:power:auxiliary_power_unit:mass:offset	power (C1): correction offset to be applied on computed mass
tuning:weight:systems:power:electric_systems:mass:k	power (C1): correction ratio to be applied on computed mass
tuning:weight:systems:power:electric_systems:mass:offset	power (C1): correction offset to be applied on computed mass
tuning:weight:systems:power:hydraulic_systems:mass:k	power (C1): correction ratio to be applied on computed mass
tuning:weight:systems:power:hydraulic_systems:mass:offset	power (C1): correction offset to be applied on computed mass
tuning:weight:systems:transmission:mass:k	transmission (C4): correction ratio to be applied on computed mass
tuning:weight:systems:transmission:mass:offset	transmission (C4): correction offset to be applied on computed mass