Understanding the Variable Metadata

How Variable Metadata Works

Every variable in an Aviary variable hierarchy must have metadata associated with it. This metadata is used for setting initial values, setting Aviary inputs and outputs, and various other functionalities throughout the code. It is also helpful information for the user to have regarding each variable and the metadata dictionary allows all that information to live in one organized location. Unlike variable hierarchies, which are broken up into different categories based on the type of information they contain, the variable metadata all lives in the same dictionary, regardless of which variable hierarchy its variables come from.

The variable metadata dictionary is exactly what it sounds like: a Python dictionary, or more explicitly a Python dictionary of dictionaries. The entire metadata is one dictionary, and within that metadata dictionary each variable (the key) has its own sub-dictionary including all the information relevant to that variable. The information included in each sub-dictionary is:

Key Name in Metadata	Default Value	Information
key	None	Name
units	unitless	Units
default_value	0.0	Default Value
types	None	Type Restrictions
multivalue	False	Can variable be vectorized?
option	False	Is Option?
desc	None	Description
historical_name	None	Historical Variable Name(s)

Many of these variables are self-explanatory, but many require additional discussion.

key is the variable name, which must be a string compatible with OpenMDAO’s variable name rules. Units must be a string, also compatible with OpenMDAO’s list of supported units.

default_value is what Aviary will use if the variable is not provided by the user as an input or does not come from another part of the problem (computed by another component, provided by Dymos as a state/control/timeseries , etc.)

types is a Python type or tuple of types that this variable is allowed to be. If not provided, types defaults to the type of default_value (which in turn is defaulted to a float).

multivalue is a boolean flag that tells Aviary if this variable can be a iterable (typically a list, numpy array, or tuple). If this flag is True, those iterable types are also allowable types in addition to whatever is listed in types. When doing type checks, Aviary will check the value of each index in a provided iterable against types. So if your variable is expected to be a list of floats, then types should be set to float, and multivalue should be True. If you provide an iterable type in types while multivalue is True, then you are telling Aviary that you can have a multidimensional array (e.g. a list that contains lists). Expected array size is not set in metadata, but instead in OpenMDAO system definition, when inputs/outputs/options are added to the system.

If multivalue is False and an iterable type is given in types, then Aviary will not know how to enforce type checks for values inside the iterable! Any iterable that matches types will pass, regardless of what it contains - this is technically fine, but opens you up to an accidental TypeError later down the line. We don’t reccomend setting up variables like this. In general, only add iterable types to types if you are working with multidimensional arrays.

option is a boolean flag if your variable is used as an OpenMDAO option, rather than a component input or output. Set this flag to True to ensure your variable correctly gets connected to any components that ask for it through options.

desc is a string that should describe what the variable represents, how it is used, and any other information that would be helpful for an aircraft designer setting a value for that variable in their input file.

historical_name is a dictionary that connects this variable with any potential matching variables in legacy codes Aviary inherrited from. Variable names under the keys FLOPS or GASP will be used by the fortran_to_aviary input file conversion utility to attempt to match legacy input files with Aviary variables.

The information in the metadata dictionary is accessed just like information in any other Python dictionary. For example, if you wanted to know the units of the Aircraft.Wing.SPAN variable from the Aviary-core Aircraft variable hierarchy along with whether or not the variable was an option, you would access those units using the following code:

import aviary.api as av

AviaryAircraft = av.Aircraft

wingspan_units = av.CoreMetaData[AviaryAircraft.Wing.SPAN]['units']
wingspan_is_option = av.CoreMetaData[AviaryAircraft.Wing.SPAN]['option']

print(wingspan_units)
print(wingspan_is_option)

In this example we use the variable hierarchy to provide the name of the variable we are seeking to Aviary’s CoreMetaData, and we use the keys from the metadata dictionary to provide the specific information that we would like to know. This would return

ft
False

which tells you that the units of the variable Aircraft.Wing.SPAN from the Aviary-core Aircraft variable hierarchy are feet, and that Aircraft.Wing.SPAN is not an option.

Note

Many of the weight and aerodynamic estimating relationships in Aviary originated from historical codes called GASP and FLOPS. For engineers who are familiar with GASP and FLOPS it is helpful to know what an Aviary variable was called in those historical codes.

The historical variable name portion of the metadata allows us to associate any names that an Aviary variable may have had in a previous code. This piece of the metadata is actually a dictionary within each subdictionary belonging to each variable. This dictionary is used by adding an entry for each historical code, where the key is the name of the historical code, and the value for that key is a string or list of strings illustrating the name(s) that variable held in the historic code. This is an optional feature, but can be helpful for users who are porting old codes into new formats. If a tilde (~) is attached to a historical variable, it is a local variable or parameter in GASP or FLOPS. More details about the naming convention is described in utils/develop_metadata.py.

The Aviary-core Metadata

The Aviary code provides metadata for every variable in the Aviary-core variable hierarchies. As noted above, the metadata is not broken up into multiple dictionaries like the variable hierarchy, but instead the metadata for every variable lives in the same dictionary. As such there is only one Aviary-core metadata dictionary, which can be viewed here and accessed in the following way:

import aviary.api as av

MetaData = av.CoreMetaData

In the Aviary-core metadata dictionary, due to the size of the data we have adopted a structure of organizing the metadata alphabetically by variable hierarchy. Thus, while all the variables are part of the same metadata dictionary, you will notice that the organization structure of the file is the same alphabetical hierarchal organization structure as the Aviary-core variable hierarchy. This is a convention that we encourage to improve the cleanliness of code, but it is not strictly required.

Building Your Own Metadata

Unlike the variable hierarchies, which are separated out into different hierarchies for different types of data, there is only one metadata dictionary for all variables in every variable hierarchy. Technically the user may build a metadata dictionary from scratch instead of extending the Aviary-core metadata, however, there is no real value to this as you will eventually have to merge back in the Aviary-core metadata anyway, so there are no normal circumstances under which this is the recommended practice. However, just like with variable hierarchies, you can have several different metadata dictionaries which will eventually be merged together. This may be necessary when there are multiple people developing different external subsystems in different locations.

There are two different ways to change the metadata in a metadata dictionary. The first is to add a new variable to the dictionary, and add that variable’s metadata along with it. This makes use of the add_meta_data() function. This function takes in the variable name of the variable to be added to the metadata dictionary be provided, as well as the dictionary itself that the variable should be added to. It also optionally takes in all of the metadata information listed at the beginning of this page. The function returns nothing, but it internally updates the provided metadata dictionary so that dictionary will contain the new variable and its metadata.

The second way to change the metadata in a metadata dictionary is by updating the metadata associated with a variable that is already in the dictionary. This is accomplished using the update_meta_data() function. This function behaves almost identically to the add_meta_data() function, the only difference being that instead of adding a new variable to the dictionary, it will take the input of metadata information that you provide and overwrite the old metadata of the given variable with the new metadata.

There are two pitfalls that may occur when using these functions. The first pitfall is attempting to call the add_meta_data() function for a variable that already exists in the metadata. This will throw an error, because the add_meta_data() function is only for new variables to the metadata. Conversely, attempting to update the metadata of a variable that is not in the metadata dictionary via update_meta_data() will throw an error because that function is only for variables that already exist in the metadata.

The methods outlined above for updating and adding to the variable metadata are the crux of how the variable metadata can be extended for new variables. The user will simply import the existing Aviary-core metadata and add to it as they see fit.

Note

The variable metadata dictionary that is imported from the Aviary API is actually a copy of the original Aviary metadata dictionary to avoid mutating the original dictionary. That being said, it functions just as a metadata dictionary that you would input to an Aviary model and you can extend it or input it to a model as-is depending on your needs.

Lets examine how we would extend the variable metadata dictionary in practice. Say we have just extended the Aviary-core Aircraft variable hierarchy to add some center of gravity, flap, and jury strut information using the extension below:

import aviary.api as av

AviaryAircraft = av.Aircraft


class ExtendedAircraft(AviaryAircraft):
    CG = 'aircraft:center_of_gravity'

    class Wing(AviaryAircraft.Wing):
        class Flap:
            AREA = 'aircraft:wing:flap:area'
            ROOT_CHORD = 'aircraft:wing:flap:root_chord'
            SPAN = 'aircraft:wing:flap:span'

    class Jury:
        MASS = 'aircraft:jury:mass'

Now we want to extend the Aviary-core metadata into our own metadata that includes metadata for each one of these variables in the same code:

ExtendedMetaData = av.CoreMetaData

av.add_meta_data(
    ExtendedAircraft.CG,
    meta_data=av.CoreMetaData,
    units='ft',
    desc='Center of gravity',
    default_value=0,
    option=False,
)

av.add_meta_data(
    ExtendedAircraft.Wing.Flap.AREA,
    meta_data=ExtendedMetaData,
    units='ft**2',
    desc='planform area of flap',
    default_value=10,
    option=False,
)

av.add_meta_data(
    ExtendedAircraft.Wing.Flap.ROOT_CHORD,
    meta_data=ExtendedMetaData,
    units='ft',
    desc='chord of flap at root of wing',
    default_value=1,
    option=False,
)

av.add_meta_data(
    ExtendedAircraft.Wing.Flap.SPAN,
    meta_data=ExtendedMetaData,
    units='ft',
    desc='span of flap',
    default_value=60,
    option=False,
)

av.add_meta_data(
    ExtendedAircraft.Jury.MASS,
    meta_data=ExtendedMetaData,
    units='kg',
    desc='mass of jury strut',
    default_value=50,
    option=False,
)

ExtendedMetaData now contains the metadata of all the Aviary-core variables along with the metadata information that we just added.

Merging Independent Metadata

Extending the metadata is great, but sometimes users will end up with multiple metadata dictionaries because different subsystem developers extended the metadata (and created associated variable hierarchies) to suit their own needs. Aviary needs to be given one single metadata dictionary which contains metadata of all the variables it has been given, so we need to be able to merge together multiple metadata dictionaries into one. The merge_meta_data() function has been provided to combine all the different metadata into one. The merge_meta_data() function behaves quite similarly to the merge_hierarchies() function. It takes in a string of metadata dictionaries that need to be merged together, and it returns a single metadata dictionary containing the metadata from all the individual dictionaries.

Let’s say that we have created our ExtendedAircraft and ExtendedMetaData from above, and that elsewhere we have a subsystem that requires information about engine cooling system mass as well as whether the aircraft has winglets. Below is the buildup of the Aircraft type hierarchy and the metadata for our new subsystem:

import aviary.api as av


class ExtendedAircraft2(av.Aircraft):
    class Engine(av.Aircraft.Engine):
        class Cooling:
            MASS = 'aircraft:engine:cooling:mass'

    class Wing(av.Aircraft.Wing):
        WINGLETS = 'aircraft:wing:winglets'


ExtendedMetaData2 = av.CoreMetaData

av.add_meta_data(
    ExtendedAircraft2.Engine.Cooling.MASS,
    units='kg',
    desc='mass of cooling system for one engine',
    default_value=100,
    meta_data=ExtendedMetaData2,
    historical_name=None,
)

av.add_meta_data(
    ExtendedAircraft2.Wing.WINGLETS,
    units=None,
    desc='Tells whether the aircraft has winglets',
    default_value=True,
    option=True,
    types=bool,
    meta_data=ExtendedMetaData2,
    historical_name=None,
)

# Testing Cell
glue_variable(get_variable_name(ExtendedAircraft2), md_code=True)
glue_variable(get_variable_name(ExtendedMetaData2), md_code=True)

We can see from the above code that we have an Aircraft type variable hierarchy named ExtendedAircraft2 and that we have created our own metadata dictionary ExtendedMetaData2 which is an extension of the CoreMetaData dictionary in Aviary-core. Now we have two different Aircraft type variable hierarchy extensions, ExtendedAircraft and ExtendedAircraft2. We also have two different metadata extensions, ExtendedMetaData and ExtendedMetaData2. We need a single Aircraft type variable hierarchy, and single metadata dictionary. Thus, we will use the merging functions built into Aviary:

FinalAircraft = av.merge_hierarchies([ExtendedAircraft, ExtendedAircraft2])
FinalMetaData = av.merge_meta_data([ExtendedMetaData, ExtendedMetaData2])

Above we merged together our hierarchy and metadata extensions, and now we have one single Aircraft type hierarchy FinalAircraft and one single metadata dictionary FinalMetaData which we can provide to the Aviary model.

There is one situation when an attempt to merge together multiple metadata dictionaries will cause errors, and that situation is if more than one metadata dictionary contains the same variable with different metadata. If multiple dictionaries contain the same variable with identical metadata the merge will proceed, but if the metadata differs at all the merge will halt and force the user to rectify the discrepancy.

More syntactical data on the merging functions can be found here.

Providing Aviary with Necessary Variable Metadata

This section is under development.

Searchable Metadata Table

The table below contains all the metadata for every variable in the Aviary-core variable hierarchies. The table is searchable and sortable and is created automatically from the Aviary core metadata dictionary.

ⓘvariable name	units	desc	option	default_value	types	multivalue	historical_name
aircraft:air_conditioning:mass	lbm	Environmental control mass (air conditioning)	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:air_conditioning:mass_coefficient	unitless	mass trend coefficient of air conditioning	False	1.0	<class 'float'>	False	GASP: INGASP.CW(6)<br />FLOPS: None
aircraft:air_conditioning:mass_scaler	unitless	air conditioning system mass scaler	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.WAC
aircraft:anti_icing:mass	lbm	Anti-icing system mass	False	0.0	<class 'float'>	False	GASP: INGASP.CW(7)<br />FLOPS: None
aircraft:anti_icing:mass_scaler	unitless	anti-icing system mass scaler	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.WAI
aircraft:apu:mass	lbm	mass of auxiliary power unit	False	0.0	<class 'float'>	False	GASP: INGASP.CW(1)<br />FLOPS: None
aircraft:apu:mass_scaler	unitless	mass scaler for auxiliary power unit	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.WAPU
aircraft:avionics:mass	lbm	Avionics group mass. Includes equipment and installation mass.	False	0.0	<class 'float'>	False	GASP: INGASP.CW(5)<br />FLOPS: None
aircraft:avionics:mass_scaler	unitless	avionics mass scaler	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.WAVONC
aircraft:battery:additional_mass	lbm	mass of non energy-storing parts of the battery	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:battery:discharge_limit	unitless	default constraint on how far the battery can discharge, as a proportion of total energy capacity	False	0.2	<class 'float'>	False	GASP: INGASP.SOCMIN<br />FLOPS: None
aircraft:battery:efficiency	unitless	battery pack efficiency	False	1.0	<class 'float'>	False	GASP: INGASP.EFF_BAT<br />FLOPS: None
aircraft:battery:energy_capacity	kJ	total energy the battery can store	False	0.0	<class 'float'>	False	GASP: EBATTAVL<br />FLOPS: None
aircraft:battery:mass	lbm	total mass of the battery	False	0.0	<class 'float'>	False	GASP: INGASP.WBATTIN<br />FLOPS: None
aircraft:battery:pack_energy_density	W*h/kg	specific energy density of the battery pack	False	1.0	<class 'float'>	False	GASP: INGASP.ENGYDEN<br />FLOPS: None
aircraft:battery:pack_mass	lbm	mass of the energy-storing components of the battery	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:battery:pack_volumetric_density	kW*h/L	volumetric density of the battery pack	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:battery:volume	ft*3	total volume of the battery pack	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:blended_wing_body_design:detailed_wing_provided	unitless	Flag if the detailed wing model is provided	True	True	<class 'bool'>	False	GASP: None<br />FLOPS: None
aircraft:blended_wing_body_design:max_bay_width	ft	maximum bay width	True	0	<class 'float'>	False	GASP: None<br />FLOPS: FUSEIN.BAYWMX<br />LEAPS1: None
aircraft:blended_wing_body_design:max_num_bays	unitless	fixed number of bays	True	0	<class 'int'>	False	GASP: None<br />FLOPS: FUSEIN.NBAYMX
aircraft:blended_wing_body_design:num_bays	unitless	fixed number of passenger bays	False	[0]	<class 'int'>	True	GASP: None<br />FLOPS: FUSEIN.NBAY
aircraft:blended_wing_body_design:passenger_leading_edge_sweep	deg	forebody sweep angle	False	0.0	<class 'float'>	False	GASP: ['INGASP.SWP_FB']<br />FLOPS: FUSEIN.SWPLE
aircraft:canard:area	ft**2	canard theoretical area	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.SCAN
aircraft:canard:aspect_ratio	unitless	canard theoretical aspect ratio	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.ARCAN
aircraft:canard:characteristic_length	ft	Reynolds characteristic length for the canard	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:canard:fineness	unitless	canard fineness ratio	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:canard:laminar_flow_lower	unitless	define percent laminar flow for canard lower surface	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: AERIN.TRLC
aircraft:canard:laminar_flow_upper	unitless	define percent laminar flow for canard upper surface	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: AERIN.TRUC
aircraft:canard:mass	lbm	mass of canards	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:canard:mass_scaler	unitless	mass scaler for canard structure	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.FRCAN
aircraft:canard:taper_ratio	unitless	canard theoretical taper ratio	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.TRCAN
aircraft:canard:thickness_to_chord	unitless	canard thickness-chord ratio	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.TCCAN
aircraft:canard:wetted_area	ft**2	canard wetted area	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:canard:wetted_area_scaler	unitless	canard wetted area scaler	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: AERIN.SWETC
aircraft:controls:cockpit_control_mass	lbm	cockpit controls mass	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:controls:cockpit_control_mass_scaler	unitless	technology factor on cockpit controls mass	False	1.0	<class 'float'>	False	GASP: INGASP.CK15<br />FLOPS: None
aircraft:controls:control_mass_increment	lbm	incremental flight controls mass	False	0.0	<class 'float'>	False	GASP: INGASP.DELWFC<br />FLOPS: None
aircraft:controls:mass	lbm	Flight controls group mass. Contains cockpit controls, automatic flight control system and system controls.	False	0.0	<class 'float'>	False	GASP: INGASP.WFC<br />FLOPS: None
aircraft:controls:stability_augmentation_system_mass	lbm	scaled mass of stability augmentation system	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:controls:stability_augmentation_system_mass_scaler	unitless	technology factor on stability augmentation system mass	False	1.0	<class 'float'>	False	GASP: INGASP.CK19<br />FLOPS: None
aircraft:controls:stability_augmentation_system_reference_mass	lbm	reference mass of stability augmentation system	False	0.0	<class 'float'>	False	GASP: INGASP.SKSAS<br />FLOPS: None
aircraft:crew_and_payload:baggage_mass	lbm	mass of passenger baggage	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:crew_and_payload:baggage_mass_per_passenger	lbm	baggage mass per passenger	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.BPP
aircraft:crew_and_payload:cabin_crew_mass	lbm	total mass of the non-flight crew and their baggage	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:crew_and_payload:cabin_crew_mass_scaler	unitless	scaler for total mass of the non-flight crew and their baggage	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.WSTUAB
aircraft:crew_and_payload:cargo_container_mass	lbm	mass of cargo containers	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:crew_and_payload:cargo_container_mass_scaler	unitless	Scaler for mass of cargo containers	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.WCON
aircraft:crew_and_payload:cargo_mass	lbm	total mass of as-flown cargo	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:crew_and_payload:catering_items_mass_per_passenger	lbm	mass of catering items per passenger	False	0.0	<class 'float'>	False	GASP: INGASP.CW(12)<br />FLOPS: None
aircraft:crew_and_payload:flight_crew_mass	lbm	total mass of the flight crew and their baggage	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:crew_and_payload:flight_crew_mass_scaler	unitless	scaler for total mass of the flight crew and their baggage	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.WFLCRB
aircraft:crew_and_payload:mass_per_passenger	lbm	mass per passenger	False	165.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.WPPASS
aircraft:crew_and_payload:mass_per_passenger_with_bags	lbm	total mass of one passenger and their bags	False	200.0	<class 'float'>	False	GASP: INGASP.UWPAX<br />FLOPS: None
aircraft:crew_and_payload:misc_cargo	lbm	cargo (other than passenger baggage) carried in fuselage	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.CARGOF
aircraft:crew_and_payload:num_business_class	unitless	number of business class passengers	True	0	<class 'int'>	False	GASP: None<br />FLOPS: None
aircraft:crew_and_payload:num_cabin_crew	unitless	Total number of cabin crew. In FLOPS this includes galley and flight attendants	True	0	<class 'int'>	False	GASP: None<br />FLOPS: None
aircraft:crew_and_payload:num_economy_class	unitless	number of economy class passengers	True	0	<class 'int'>	False	GASP: None<br />FLOPS: None
aircraft:crew_and_payload:num_first_class	unitless	number of first class passengers.	True	0	<class 'int'>	False	GASP: None<br />FLOPS: None
aircraft:crew_and_payload:num_flight_attendants	unitless	number of flight attendants	True	0	<class 'int'>	False	GASP: None<br />FLOPS: WTIN.NSTU
aircraft:crew_and_payload:num_flight_crew	unitless	number of flight crew	True	0	<class 'int'>	False	GASP: None<br />FLOPS: WTIN.NFLCR
aircraft:crew_and_payload:num_galley_crew	unitless	number of galley crew	True	0	<class 'int'>	False	GASP: None<br />FLOPS: WTIN.NGALC
aircraft:crew_and_payload:num_passengers	unitless	total number of passengers	True	0	<class 'int'>	False	GASP: None<br />FLOPS: None
aircraft:crew_and_payload:passenger_mass_total	lbm	TBD: total mass of all passengers without their baggage	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:crew_and_payload:passenger_payload_mass	lbm	mass of passenger payload, including passengers, passenger baggage	False	0.0	<class 'float'>	False	GASP: INGASP.WPL<br />FLOPS: None
aircraft:crew_and_payload:passenger_service_mass	lbm	mass of passenger service equipment	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:crew_and_payload:passenger_service_mass_per_passenger	lbm	mass of passenger service items mass per passenger	False	0.0	<class 'float'>	False	GASP: INGASP.CW(9)<br />FLOPS: None
aircraft:crew_and_payload:passenger_service_mass_scaler	unitless	scaler for mass of passenger service equipment	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.WSRV
aircraft:crew_and_payload:total_payload_mass	lbm	total mass of payload, including passengers, passenger baggage, and cargo	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:crew_and_payload:uld_mass_per_passenger	lbm	unit mass of ULD (unit load device) for cargo handling per passenger. Used to calculateAicraft.CrewPayload.CARGO_CONTAINER_MASS	True	0.0	<class 'float'>	False	GASP: INGASP.CW(14)<br />FLOPS: None
aircraft:crew_and_payload:water_mass_per_occupant	lbm	mass of water per occupant (passengers, pilots, and flight attendants)	False	1.0	<class 'float'>	False	GASP: INGASP.CW(10)<br />FLOPS: None
aircraft:crew_and_payload:wing_cargo	lbm	cargo carried in wing	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.CARGOW
aircraft:crew_and_payload:design:cargo_mass	lbm	total mass of cargo flown on design mission	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:crew_and_payload:design:max_cargo_mass	lbm	maximum mass of cargo	False	0.0	<class 'float'>	False	GASP: INGASP.WCARGO<br />FLOPS: None
aircraft:crew_and_payload:design:num_business_class	unitless	number of business class passengers that the aircraft is designed to accommodate	True	0	<class 'int'>	False	GASP: None<br />FLOPS: WTIN.NPB
aircraft:crew_and_payload:design:num_economy_class	unitless	number of economy class passengers that the aircraft is designed to accommodate	True	0	<class 'int'>	False	GASP: None<br />FLOPS: WTIN.NPT
aircraft:crew_and_payload:design:num_first_class	unitless	number of first class passengers that the aircraft is designed to accommodate. In GASP, the input is the percentage of total number of passengers.	True	0	<class 'int'>	False	GASP: INGASP.PCT_FC<br />FLOPS: WTIN.NPF
aircraft:crew_and_payload:design:num_passengers	unitless	total number of passengers that the aircraft is designed to accommodate	True	0	<class 'int'>	False	GASP: INGASP.PAX<br />FLOPS: None
aircraft:crew_and_payload:design:num_seats_abreast_business	unitless	Number of business class seats abreast.	True	5	<class 'int'>	False	GASP: None<br />FLOPS: FUSEIN.NBABR
aircraft:crew_and_payload:design:num_seats_abreast_economy	unitless	Number of economy class seats abreast.	True	6	<class 'int'>	False	GASP: INGASP.SAB<br />FLOPS: FUSEIN.NTABR
aircraft:crew_and_payload:design:num_seats_abreast_first	unitless	Number of first class seats abreast.	True	4	<class 'int'>	False	GASP: None<br />FLOPS: FUSEIN.NFABR
aircraft:crew_and_payload:design:seat_pitch_business	inch	pitch of the business class seats.	True	39.0	<class 'float'>	False	GASP: None<br />FLOPS: FUSEIN.BPITCH
aircraft:crew_and_payload:design:seat_pitch_economy	inch	pitch of the economy class seats.	True	32.0	<class 'float'>	False	GASP: INGASP.PS<br />FLOPS: FUSEIN.TPITCH
aircraft:crew_and_payload:design:seat_pitch_first	inch	pitch of the first class seats.	True	61.0	<class 'float'>	False	GASP: None<br />FLOPS: FUSEIN.FPITCH
aircraft:design:base_area	ft**2	Aircraft base area (total exit cross-section area minus inlet capture areas for internally mounted engines)	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: AERIN.SBASE
aircraft:design:cg_delta	unitless	allowable center-of-gravity (cg) travel as a fraction of the mean aerodynamic chord	False	0.0	<class 'float'>	False	GASP: INGASP.DELCG<br />FLOPS: None
aircraft:design:characteristic_lengths	ft	Reynolds characteristic length for each component	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:design:cockpit_control_mass_coefficient	unitless	mass trend coefficient of cockpit controls	False	0.0	<class 'float'>	False	GASP: INGASP.SKCC<br />FLOPS: None
aircraft:design:compressibility_drag_factor	unitless	compressibility aero calibration factor	False	1.0	<class 'float'>	False	GASP: INGASP.FCMPC<br />FLOPS: None
aircraft:design:compute_htail_volume_coeff	unitless	if true, use empirical tail volume coefficient equation. This is true if VBARHX is 0 in GASP.	True	False	<class 'bool'>	False	GASP: None<br />FLOPS: None
aircraft:design:compute_vtail_volume_coeff	unitless	if true, use empirical tail volume coefficient equation. This is true if VBARVX is 0 in GASP.	True	False	<class 'bool'>	False	GASP: None<br />FLOPS: None
aircraft:design:cruise_altitude	ft	design mission cruise altitude	True	25000.0	<class 'float'>	False	GASP: INGASP.CRALT<br />FLOPS: None
aircraft:design:cruise_mach	unitless	aircraft cruise Mach number	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: CONFIN.VCMN
aircraft:design:drag_coefficient_increment	unitless	increment to the profile drag coefficient	False	0.0	<class 'float'>	False	GASP: INGASP.DELCD<br />FLOPS: None
aircraft:design:drag_divergence_shift	unitless	shift in drag divergence Mach number due to supercritical design	False	0.0	<class 'float'>	False	GASP: INGASP.SCFAC<br />FLOPS: None
aircraft:design:drag_polar	unitless	Drag polar computed during Aviary pre-mission.	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
aircraft:design:emergency_equipment_mass	lbm	mass of emergency equipment	False	0.0	<class 'float'>	False	GASP: INGASP.CW(11)<br />FLOPS: None
aircraft:design:empennage_mass	lbm	Empennage group mass. Contains mass of canards, horizontal/vertical stabilizers and fins, and ventral fins, and any supporting structure for mounted engines on those surfaces.	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:design:empty_mass	lbm	Empty mass of the aircraft. Includes structure group, propulsion group, and total systems and equipment mass.	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:design:empty_mass_margin	lbm	empty mass margin	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:design:empty_mass_margin_scaler	unitless	empty mass margin scaler	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.EWMARG
aircraft:design:excrescence_drag_factor	unitless	excrescence aero drag factor	False	1.0	<class 'float'>	False	GASP: INGASP.FEXCRT<br />FLOPS: None
aircraft:design:external_subsystems_mass	lbm	Total mass of all user-defined external subsystems. These are bookkept as part of empty mass.	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:design:fineness	unitless	table of component fineness ratios	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:design:gross_mass	lbm	Design gross mass of the aircraft. Includes zero fuel mass plus useable fuel.	False	0.0	<class 'float'>	False	GASP: INGASP.WG<br />FLOPS: WTIN.DGW
ijeff	unitless	A flag used by Jeff V. Bowles to debug GASP code during his 53 years supporting the development of GASP. This flag is planted here to thank him for his hard work and dedication, Aviary wouldn't be what it is today without his help.	False	0.0	<class 'float'>	False	GASP: INGASP.IJEFF<br />FLOPS: None
aircraft:design:interference_drag_factor	unitless	interference aero calibration factor (including technology factor INGASP.FCKIT)	False	1.0	<class 'float'>	False	GASP: INGASP.FCKIC<br />FLOPS: None
aircraft:design:laminar_flow_lower	unitless	table of percent laminar flow over lower component surfaces	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:design:laminar_flow_upper	unitless	table of percent laminar flow over upper component surfaces	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:design:landing_to_takeoff_mass_ratio	unitless	ratio of maximum landing mass to maximum takeoff mass	False	1.0	<class 'float'>	False	GASP: INGASP.WLPCT<br />FLOPS: AERIN.WRATIO
aircraft:design:lift_coefficient	unitless	Fixed design lift coefficient. If input, overrides design lift coefficient computed by EDET.	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: AERIN.FCLDES
aircraft:design:lift_coefficient_max_flaps_up	unitless	maximum lift coefficient from flaps model when flaps are up (not deployed)	False	0.0	<class 'float'>	False	GASP: ['INGASP.CLMWFU', 'INGASP.CLMAX']<br />FLOPS: None
aircraft:design:lift_curve_slope	1/rad	lift curve slope at cruise Mach number	False	0.0	<class 'float'>	False	GASP: INGASP.CLALPH<br />FLOPS: None
aircraft:design:lift_dependent_drag_coeff_factor	unitless	Scaling factor for lift-dependent drag coefficient	False	1.0	<class 'float'>	False	GASP: INGASP.FSA7C<br />FLOPS: MISSIN.FCDI
aircraft:design:lift_dependent_drag_polar	unitless	Lift dependent drag polar computed during Aviary pre-mission.	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
aircraft:design:lift_independent_drag_polar	unitless	Lift independent drag polar computed during Aviary pre-mission.	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
aircraft:design:lift_polar	unitless	Lift polar computed during Aviary pre-mission.	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
aircraft:design:mach	unitless	aircraft design Mach number	False	0.0	<class 'float'>	False	GASP: INGASP.CRMACH<br />FLOPS: AERIN.FMDES
aircraft:design:max_fuselage_pitch_angle	deg	maximum fuselage pitch allowed	False	15.0	<class 'float'>	False	GASP: INGASP.THEMAX<br />FLOPS: None
aircraft:design:max_structural_speed	mi/h	maximum structural design flight speed in miles per hour	False	0.0	<class 'float'>	False	GASP: INGASP.VMLFSL<br />FLOPS: None
aircraft:design:part25_structural_category	unitless	part 25 structural category	True	3	<class 'int'>	False	GASP: INGASP.CATD<br />FLOPS: None
aircraft:design:percent_excrescence_drag	unitless	excrescence drag as percentage of fuselage, wing, nacelle, (winglet), empennage and strut	True	0.0	<class 'float'>	False	GASP: INGASP.PCT_EXCR<br />FLOPS: None
aircraft:design:range	NM	The design range of the aircraft used for sizing of FLOPS based subsystems and mission target length if not provided in phase_info	False	0.0	<class 'float'>	False	GASP: INGASP.ARNGE<br />FLOPS: CONFIN.DESRNG
aircraft:design:smooth_mass_discontinuities	unitless	eliminates discontinuities in GASP-based mass estimation code if true	True	False	<class 'bool'>	False	GASP: None<br />FLOPS: None
aircraft:design:static_margin	unitless	aircraft static margin as a fraction of mean aerodynamic chord	False	0.0	<class 'float'>	False	GASP: INGASP.STATIC<br />FLOPS: None
aircraft:design:structural_mass_increment	lbm	structural mass increment that is added (or removed) after the structural mass is calculated	False	0.0	<class 'float'>	False	GASP: INGASP.DELWST<br />FLOPS: None
aircraft:design:structure_mass	lbm	Total structure group mass. Includes the following groups: wing, epennage, fuselage, landing gear, air induction.	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:design:subsonic_drag_coeff_factor	unitless	Scaling factor for subsonic drag	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: MISSIN.FCDSUB
aircraft:design:supersonic_drag_coeff_factor	unitless	Scaling factor for supersonic drag	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: MISSIN.FCDSUP
aircraft:design:systems_and_equipment_mass	lbm	Systems and equipment group mass. Includes flight controls, auxilary power, instruments, hydraulics, pneumatics, electrical, avionics, furnishings and equipment, environmental control, and anti-icing mass.	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:design:systems_and_equipment_mass_base	lbm	Total systems & equipment group mass without additional 1% of empty mass	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:design:thrust_to_weight_ratio	unitless	ratio of total sea-level-static thrust to aircraft takeoff gross weight	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:design:total_wetted_area	ft**2	total aircraft wetted area	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:design:touchdown_mass_max	lbm	Maximum mass at touchdown used to size landing gear	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.WLDG
aircraft:design:type	unitless	aircraft type: BWB for blended wing body, transport otherwise	True	AircraftTypes.TRANSPORT	(AircraftTypes.TRANSPORT, AircraftTypes.BLENDED_WING_BODY)	False	GASP: INGASP.IHWB<br />FLOPS: ['OPTION.IFITE']
aircraft:design:ulf_calculated_from_maneuver	unitless	if true, ULF (ultimate load factor) is forced to be calculated from the maneuver load factor, even if the gust load factor is larger. This was set to true with a negative CATD in GASP.	True	False	<class 'bool'>	False	GASP: CATD<br />FLOPS: None
aircraft:design:use_alt_mass	unitless	control whether the alternate mass equations are to be used or not	True	False	<class 'bool'>	False	GASP: None<br />FLOPS: WTIN.IALTWT
aircraft:design:useful_load_mass	lbm	Useful load of the aircraft is the difference between the max_gross_mass and the empty_mass.This includes operating_items, total_payload and total_fuel.	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:design:wetted_areas	ft**2	table of component wetted areas	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:design:wing_loading	lbf/ft**2	ratio of aircraft gross takeoff weight to projected wing area	False	0	<class 'float'>	False	GASP: ['INGASP.WGS', 'INGASP.WOS']<br />FLOPS: None
aircraft:design:zero_lift_drag_coeff_factor	unitless	Scaling factor for zero-lift drag coefficient	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: MISSIN.FCDO
aircraft:electrical:has_hybrid_system	unitless	if true there is an augmented electrical system	True	False	<class 'bool'>	False	GASP: None<br />FLOPS: None
aircraft:electrical:hybrid_cable_length	ft	length of cable for hybrid electric augmented system	False	0.0	<class 'float'>	False	GASP: INGASP.LCABLE<br />FLOPS: None
aircraft:electrical:mass	lbm	mass of the electrical system	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:electrical:mass_scaler	unitless	mass scaler for the electrical system	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.WELEC
aircraft:electrical:system_mass_per_passenger	lbm	electrical system weight per passenger. In GASP, default 16.0	False	0.0	<class 'float'>	False	GASP: INGASP.CW(15)<br />FLOPS: None
aircraft:engine:additional_mass	lbm	additional engine mass not counted by existing categories (such as engine control and starter mass in FLOPS). In GASP, this is engine installation mass.	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
aircraft:engine:additional_mass_fraction	unitless	fraction of (scaled) engine mass used to calculate additional engine mass (see Aircraft.Engine.ADDITIONAL_MASS)	True	0.0	(<class 'float'>, <class 'int'>, <class 'numpy.ndarray'>)	True	GASP: INGASP.SKPEI<br />FLOPS: WTIN.WPMISC
aircraft:engine:constant_fuel_mass_consumption	lbm/h	Additional constant fuel flow. This value is not scaled with the engine	True	0.0	<class 'float'>	True	GASP: None<br />FLOPS: MISSIN.FLEAK
aircraft:engine:data_file	unitless	filepath to data file containing engine performance tables	True	None	<class 'str'>	True	GASP: None<br />FLOPS: ENGDIN.EIFILE
aircraft:engine:fixed_rpm	rpm	RPM the engine is set to be running at. Overrides RPM provided by engine model or chosen by optimizer. Typically used when pairing a motor or turboshaft using a fixed operating RPM with a propeller.	True	1.0	<class 'float'>	True	GASP: None<br />FLOPS: None
aircraft:engine:flight_idle_max_fraction	unitless	If Aircraft.Engine.GENERATE_FLIGHT_IDLE is True, bounds engine performance outputs (other than thrust) at flight idle to be below a decimal fraction of the max value of that output produced by the engine at each flight condition.	True	1.0	<class 'float'>	True	GASP: None<br />FLOPS: ENGDIN.FIDMAX
aircraft:engine:flight_idle_min_fraction	unitless	If Aircraft.Engine.GENERATE_FLIGHT_IDLE is True, bounds engine performance outputs (other than thrust) at flight idle to be above a decimal fraction of the max value of that output produced by the engine at each flight condition.	True	0.08	<class 'float'>	True	GASP: None<br />FLOPS: ENGDIN.FIDMIN
aircraft:engine:flight_idle_thrust_fraction	unitless	If Aircraft.Engine.GENERATE_FLIGHT_IDLE is True, defines idle thrust condition as a decimal fraction of max thrust produced by the engine at each flight condition.	True	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
aircraft:engine:fuel_flow_scaler_constant_term	unitless	Constant term in fuel flow scaling equation	True	0.0	<class 'float'>	True	GASP: None<br />FLOPS: ENGDIN.DFFAC
aircraft:engine:fuel_flow_scaler_linear_term	unitless	Linear term in fuel flow scaling equation	True	0.0	<class 'float'>	True	GASP: None<br />FLOPS: ENGDIN.FFFAC
aircraft:engine:generate_flight_idle	unitless	If True, generate flight idle data by extrapolating from engine data. Flight idle is defined as engine performance when thrust is reduced to the level defined by Aircraft.Engine.FLIGHT_IDLE_THRUST_FRACTION. Other engine outputs are extrapolated to this thrust level, bounded by Aircraft.Engine.FLIGHT_IDLE_MIN_FRACT and Aircraft.Engine.FLIGHT_IDLE_MAX_FRACT	True	False	<class 'bool'>	True	GASP: None<br />FLOPS: ENGDIN.IDLE
aircraft:engine:geopotential_alt	unitless	If True, engine deck altitudes are geopotential and will be converted to geometric altitudes. If False, engine deck altitudes are geometric.	True	False	<class 'bool'>	True	GASP: None<br />FLOPS: ENGDIN.IGEO
aircraft:engine:global_hybrid_throttle	unitless	Flag for engine decks if the range of provided hybrid throttles is consistent across all flight conditions (e.g. the maximum hybrid throttle seen in the entire deck is 1.0, but a given flight condition only goes to 0.9 -> GLOBAL_HYBRID_THROTTLE = TRUE means the engine can be extrapolated out to 1.0 at that point. If GLOBAL_HYBRID_THROTTLE is False, then each flight condition's hybrid throttle range is individually normalized from 0 to 1 independent of other points on the deck).	True	False	<class 'bool'>	True	GASP: None<br />FLOPS: None
aircraft:engine:global_throttle	unitless	Flag for engine decks if the range of provided throttles is consistent across all flight conditions (e.g. the maximum throttle seen in the entire deck is 1.0, but a given flight condition only goes to 0.9 -> GLOBAL_THROTTLE = TRUE means the engine can be extrapolated out to 1.0 at that point. If GLOBAL_THROTTLE is False, then each flight condition's throttle range is individually normalized from 0 to 1 independent of other points on the deck).	True	False	<class 'bool'>	True	GASP: None<br />FLOPS: None
aircraft:engine:ignore_negative_thrust	unitless	If False, all input or generated points are used, otherwise points in the engine deck with negative net thrust are ignored.	True	False	<class 'bool'>	True	GASP: None<br />FLOPS: ENGDIN.NONEG
aircraft:engine:inlet_area_coefficient	unitless	engine inlet area coefficient. Suggested values: 0.000375 for modern engines.	False	0.0002	<class 'float'>	True	GASP: None<br />FLOPS: None
aircraft:engine:interpolation_method	unitless	method used for interpolation on an engine deck's data file, allowable values are table methods from openmdao.components.interp_util.interp. Engine models only use the methods avilable to the MetaModelSemiStructuredComp component. These are listed here: https://openmdao.org/newdocs/versions/latest/features/building_blocks/components/metamodelsemistructured_comp.html	True	slinear	<class 'str'>	True	GASP: None<br />FLOPS: None
aircraft:engine:interpolation_sort	unitless	Specify the first interpolation variable in the semi-structured metamodel. Choose from mach or altitude. Mach is usually the first column in the deck, but altitude is more robust for semi-structured data.	True	mach	<class 'str'>	True	GASP: None<br />FLOPS: None
aircraft:engine:mass	lbm	Scaled mass of a single engine. Engine mass includes installation mass, accessory gear boxes & drive, exhaust system, engine cooling, water injection, engien controls starting system, propeller/fan installation, lubricating system, and the drive system. Drive system mass contains gearboxes including lubrication and rotor brakes, transmission drive, rotor shaft, and gas drive. Fuel system is bookept as a separate line item in the propulsion group. For nonconventional engines, such as all-electric, engine mass should also contain masses appropriate for per-engine mass bookeeping (such as motor mass).	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
aircraft:engine:mass_scaler	unitless	scaler for engine mass	False	1.0	<class 'float'>	True	GASP: INGASP.CK5<br />FLOPS: WTIN.EEXP
aircraft:engine:mass_specific	lbm/lbf	specific mass of one engine (engine weight/SLS thrust)	False	0.0	<class 'float'>	True	GASP: INGASP.SWSLS<br />FLOPS: None
aircraft:engine:num_engines	unitless	total number of engines per model on the aircraft (fuselage, wing, or otherwise)	True	2	<class 'int'>	True	GASP: INGASP.ENP<br />FLOPS: None
aircraft:engine:num_fuselage_engines	unitless	number of fuselage mounted engines per model	True	0	<class 'int'>	True	GASP: None<br />FLOPS: WTIN.NEF
aircraft:engine:num_wing_engines	unitless	number of wing mounted engines per model	True	0	<class 'int'>	True	GASP: None<br />FLOPS: WTIN.NEW
aircraft:engine:pod_mass	lbm	engine pod mass including nacelles	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
aircraft:engine:pod_mass_scaler	unitless	technology factor on mass of engine pods	False	1.0	<class 'float'>	True	GASP: INGASP.CK14<br />FLOPS: None
aircraft:engine:pylon_factor	unitless	factor for turbofan engine pylon mass	False	0.7	<class 'float'>	True	GASP: INGASP.FPYL<br />FLOPS: None
aircraft:engine:reference_mass	lbm	Unscaled mass of a single engine. See Aircraft.Engine.MASS for breakdown of what is included in engine mass.	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: WTIN.WENG
aircraft:engine:reference_sls_thrust	lbf	Maximum sea-level static thrust of an unscaled engine. Optional. In EngineDecks, reference thrust will be found from performance data if not provided by user. User-provided values override SLS point found in performance data.	False	0.0	<class 'float'>	True	GASP: INGASP.FN_REF<br />FLOPS: WTIN.THRSO
aircraft:engine:rpm_design	rpm	the designed output RPM from the engine for fixed-RPM shafts	True	0.0	<class 'float'>	True	GASP: INPROP.XNMAX<br />FLOPS: None
aircraft:engine:scale_factor	unitless	A scaling factor used to scale engine performance data during mission analysis.	False	1.0	<class 'float'>	True	GASP: None<br />FLOPS: None
aircraft:engine:scale_mass	unitless	Toggle for enabling scaling of engine mass based on Aircraft.Engine.SCALE_FACTOR	True	True	<class 'bool'>	True	GASP: None<br />FLOPS: None
aircraft:engine:scaled_sls_thrust	lbf	Maximum sea-level static thrust of an engine after scaling. Optional for EngineDecks if Aircraft.Engine.SCALE_FACTOR is provided, in which case this variable is computed.	False	0.0	<class 'float'>	True	GASP: INGASP.THIN<br />FLOPS: CONFIN.THRUST
aircraft:engine:subsonic_fuel_flow_scaler	unitless	scaling factor on fuel flow when Mach number is subsonic	True	1.0	<class 'float'>	True	GASP: INGASP.CKFF<br />FLOPS: ENGDIN.FFFSUB
aircraft:engine:supersonic_fuel_flow_scaler	unitless	scaling factor on fuel flow when Mach number is supersonic	True	1.0	<class 'float'>	True	GASP: INGASP.CKFF<br />FLOPS: ENGDIN.FFFSUP
aircraft:engine:thrust_reversers_mass	lbm	mass of thrust reversers on engines	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
aircraft:engine:thrust_reversers_mass_scaler	unitless	scaler for mass of thrust reversers on engines. In FLOPS default to 0.0	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: WTIN.WTHR
aircraft:engine:type	unitless	specifies engine type used for GASP-based engine mass calculation	True	GASPEngineType.TURBOJET	(GASPEngineType.RECIP_CARB, GASPEngineType.RECIP_FUEL_INJECT, GASPEngineType.RECIP_FUEL_INJECT_GEARED, GASPEngineType.ROTARY, GASPEngineType.TURBOSHAFT, GASPEngineType.TURBOPROP, GASPEngineType.TURBOJET, GASPEngineType.RECIP_CARB_HOPWSZ, GASPEngineType.RECIP_FUEL_INJECT_HOPWSZ, GASPEngineType.RECIP_FUEL_INJECT_GEARED_HOPWSZ, GASPEngineType.ROTARY_RCWSZ)	True	GASP: INGASP.NTYE<br />FLOPS: None
aircraft:engine:wing_locations	unitless	Engine wing mount locations as fractions of semispan; (NUM_WING_ENGINES)/2 values are input	False	[0.0]	(<class 'float'>, <class 'list'>, <class 'numpy.ndarray'>)	True	GASP: INGASP.YP<br />FLOPS: WTIN.ETAE
aircraft:engine:gearbox:efficiency	unitless	The efficiency of the gearbox.	False	1.0	<class 'float'>	True	GASP: None<br />FLOPS: None
aircraft:engine:gearbox:gear_ratio	unitless	Reduction gear ratio, or the ratio of the RPM_in divided by the RPM_out for the gearbox.	False	1.0	<class 'float'>	True	GASP: None<br />FLOPS: None
aircraft:engine:gearbox:mass	lbm	The mass of the gearbox.	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
aircraft:engine:gearbox:shaft_power_design	hp	A guess for the maximum power that will be transmitted through the gearbox during the mission (max shp input).	False	1.0	<class 'float'>	True	GASP: INPROP.HPMSLS<br />FLOPS: None
aircraft:engine:gearbox:specific_torque	lbf*ft/lbm	The specific torque of the gearbox, used to calculate gearbox mass.	False	100.0	<class 'float'>	True	GASP: None<br />FLOPS: None
aircraft:engine:motor:data_file	unitless	filepath to data file containing electric motor performance table	True	None	<class 'str'>	True	GASP: None<br />FLOPS: None
aircraft:engine:motor:mass	lbm	Total motor mass (considers number of motors)	False	0.0	<class 'float'>	True	GASP: WMOTOR<br />FLOPS: None
aircraft:engine:motor:torque_max	lbf*ft	Max torque value that can be output from a single motor. Used to determine motor mass in pre-mission	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
aircraft:engine:propeller:activity_factor	unitless	propeller actitivty factor per Blade (Range: 80 to 200)	False	0.0	<class 'float'>	True	GASP: INPROP.AF<br />FLOPS: None
aircraft:engine:propeller:compute_installation_loss	unitless	if true, compute installation loss factor based on blockage factor	True	True	<class 'bool'>	True	GASP: INPROP.FT<br />FLOPS: None
aircraft:engine:propeller:data_file	unitless	filepath to data file containing propeller data map	True	None	<class 'str'>	True	GASP: None<br />FLOPS: None
aircraft:engine:propeller:diameter	ft	propeller diameter	False	0.0	<class 'float'>	True	GASP: INPROP.DPROP<br />FLOPS: None
aircraft:engine:propeller:integrated_lift_coefficient	unitless	propeller blade integrated design lift coefficient (Range: 0.3 to 0.8)	False	0.5	<class 'float'>	True	GASP: INPROP.CLI<br />FLOPS: None
aircraft:engine:propeller:mass	lbm	mass of propellers on engine (sum of all blades)	False	0	<class 'float'>	True	GASP: None<br />FLOPS: None<br />LEAPS1: None
aircraft:engine:propeller:num_blades	unitless	number of blades per propeller	True	0	<class 'int'>	True	GASP: INPROP.BL<br />FLOPS: None
aircraft:engine:propeller:tip_mach_max	unitless	maximum allowable Mach number at propeller tip (based on helical speed)	False	1.0	<class 'float'>	True	GASP: None<br />FLOPS: None
aircraft:engine:propeller:tip_speed_max	ft/s	maximum allowable propeller linear tip speed	False	800.0	<class 'float'>	True	GASP: ['INPROP.TSPDMX', 'INPROP.TPSPDMXe']<br />FLOPS: None
aircraft:fins:area	ft**2	vertical fin theoretical area	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.SFIN
aircraft:fins:mass	lbm	mass of vertical fins	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:fins:mass_scaler	unitless	mass scaler for fin structure	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.FRFIN
aircraft:fins:num_fins	unitless	number of fins	True	0	<class 'int'>	False	GASP: None<br />FLOPS: WTIN.NFIN
aircraft:fins:taper_ratio	unitless	vertical fin theoretical taper ratio	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.TRFIN
aircraft:fuel:auxiliary_fuel_mass_capacity	lbm	fuel capacity of the auxiliary tank	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.FULAUX
aircraft:fuel:burn_per_passenger_mile	lbm/NM	average fuel burn per passenger per mile flown	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:fuel:density	lbm/galUS	fuel density (jet fuel typical density of 6.7 lbm/galUS used in the calculation of wing_capacity(if wing_capacity is not input) and in the calculation of fuel system weight.	False	6.7	<class 'float'>	False	GASP: INGASP.FUELD<br />FLOPS: WTIN.FULDEN
aircraft:fuel:fuel_system_mass	lbm	Fuel system mass. Includes tanks (both protected and unprotected), plumbing, and similar masses.	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:fuel:fuel_system_mass_coefficient	unitless	mass trend coefficient of fuel system	False	0.0	<class 'float'>	False	GASP: INGASP.SKFS<br />FLOPS: None
aircraft:fuel:fuel_system_mass_scaler	unitless	scaler for fuel system mass	False	1.0	<class 'float'>	False	GASP: INGASP.CK21<br />FLOPS: WTIN.WFSYS
aircraft:fuel:fuselage_fuel_mass_capacity	lbm	fuel capacity of the fuselage	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.FULFMX
aircraft:fuel:ignore_fuel_capacity_constraint	unitless	Flag to control enforcement of fuel_capacity constraint. If False (default) Aviary will add the excess fuel constraint and only converge if there is enough fuel capacity to complete the mission.If set True Aviary will ignore this constraint, and allow mission fuel > total_fuel_capacity. Use carefully!	False	False	<class 'bool'>	False	GASP: None<br />FLOPS: WTIN.IFUFU
aircraft:fuel:num_tanks	unitless	number of fuel tanks	True	7	<class 'int'>	False	GASP: None<br />FLOPS: WTIN.NTANK
aircraft:fuel:total_capacity	lbm	Total fuel capacity of the aircraft including wing, fuselage and auxiliary tanks. Used in generating payload-range diagram (Default = wing_capacity + fuselage_capacity + aux_capacity)	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.FMXTOT
aircraft:fuel:total_volume	galUS	Total fuel volume	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:fuel:unusable_fuel_mass	lbm	unusable fuel mass	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:fuel:unusable_fuel_mass_coefficient	unitless	mass trend coefficient of trapped fuel factor	False	0.0	<class 'float'>	False	GASP: INGASP.CW(13)<br />FLOPS: None
aircraft:fuel:unusable_fuel_mass_scaler	unitless	scaler for Unusable fuel mass	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.WUF
aircraft:fuel:volume_margin	unitless	Extra volume required in the wing fuel tank as a percentage of design mission fuel mass.Only used in GASP wing tank mass and fuel system mass sizing calculations.	False	0.0	<class 'float'>	False	GASP: INGASP.FVOL_MRG<br />FLOPS: None
aircraft:fuel:wing_fuel_fraction	unitless	fraction of total theoretical wing volume used for wing fuel	False	0.0	<class 'float'>	False	GASP: INGASP.SKWF<br />FLOPS: None
aircraft:fuel:wing_fuel_mass_capacity	lbm	fuel capacity of the auxiliary tank	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.FULWMX
aircraft:fuel:wing_ref_capacity	lbm	reference fuel volume	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.FUELRF
aircraft:fuel:wing_ref_capacity_area	unitless	reference wing area for fuel capacity	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.FSWREF
aircraft:fuel:wing_ref_capacity_term_a	unitless	scaling factor A	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.FUSCLA
aircraft:fuel:wing_ref_capacity_term_b	unitless	scaling factor B	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.FUSCLB
aircraft:fuel:wing_volume_design	ft**3	wing tank fuel volume when carrying design fuel plus fuel margin	False	0.0	<class 'float'>	False	GASP: INGASP.FVOLREQ<br />FLOPS: None
aircraft:fuel:wing_volume_geometric_max	ft**3	wing tank fuel volume based on geometry	False	0.0	<class 'float'>	False	GASP: INGASP.FVOLW_GEOM<br />FLOPS: None
aircraft:fuel:wing_volume_structural_max	ft**3	wing tank volume based on maximum wing fuel weight	False	0.0	<class 'float'>	False	GASP: INGASP.FVOLW_MAX<br />FLOPS: None
aircraft:furnishings:mass	lbm	Total furnishings mass	False	0.0	<class 'float'>	False	GASP: INGASP.CW(8)<br />FLOPS: None
aircraft:furnishings:mass_base	lbm	For FLOPS based, base furnishings system mass without additional 1% empty mass	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:furnishings:mass_scaler	unitless	Furnishings system mass scaler. In GASP based, it is applicale if gross mass > 10000 lbs and number of passengers >= 50. Set it to 0.0 if not use.	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.WFURN
aircraft:furnishings:use_empirical_equation	unitless	In GASP based, indicate whether use commonly used empirical furnishing weight equation. This applies only when gross mass > 10000 and number of passengers >= 50.	True	True	<class 'bool'>	False	GASP: None<br />FLOPS: None
aircraft:fuselage:aftbody_mass	lbm	aftbody mass	False	0.0	<class 'float'>	False	GASP: WGT_AB<br />FLOPS: None
aircraft:fuselage:aftbody_mass_per_unit_area	lbm/ft**2	aftbody structural areal unit weight	False	0.0	<class 'float'>	False	GASP: INGASP.UWT_AFT<br />FLOPS: None
aircraft:fuselage:aisle_width	inch	width of the aisles in the passenger cabin	True	24.0	<class 'float'>	False	GASP: INGASP.WAS<br />FLOPS: None
aircraft:fuselage:avg_diameter	ft	average fuselage diameter	False	0.0	<class 'float'>	False	GASP: ['INGASP.WC', 'INGASP.SWF']<br />FLOPS: None
aircraft:fuselage:cabin_area	ft**2	fixed area of passenger cabin for blended wing body transports	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: FUSEIN.ACABIN
aircraft:fuselage:characteristic_length	ft	Reynolds characteristic length for the fuselage	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:fuselage:cross_section	ft**2	fuselage cross sectional area	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:fuselage:delta_diameter	ft	mean fuselage cabin diameter minus mean fuselage nose diameter	False	0.0	<class 'float'>	False	GASP: INGASP.HCK<br />FLOPS: None
aircraft:fuselage:diameter_to_wing_span	unitless	fuselage diameter to wing span ratio	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:fuselage:drag_factor	unitless	fuselage aero calibration factor (including technology factor INGASP.FCFFT)	False	1.0	<class 'float'>	False	GASP: INGASP.FCFFC<br />FLOPS: None
aircraft:fuselage:fineness	unitless	fuselage fineness ratio	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:fuselage:flat_plate_area_increment	ft**2	increment to fuselage flat plate area	False	0.0	<class 'float'>	False	GASP: INGASP.DELFE<br />FLOPS: None
aircraft:fuselage:forebody_mass	lbm	forebody mass	False	0.0	<class 'float'>	False	GASP: WGT_FB<br />FLOPS: None
aircraft:fuselage:form_factor	unitless	fuselage form factor	False	0.0	<class 'float'>	False	GASP: INGASP.CKF<br />FLOPS: None
aircraft:fuselage:height_to_width_ratio	unitless	fuselage height-to-width ratio	False	1.0	<class 'float'>	False	GASP: INGASP.HGTqWID<br />FLOPS: WTIN.TCF
aircraft:fuselage:hydraulic_diameter	ft	the geometric mean of cabin height and cabin width	False	0.0	<class 'float'>	False	GASP: DHYDRAL<br />FLOPS: None
aircraft:fuselage:laminar_flow_lower	unitless	define percent laminar flow for fuselage lower surface	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: AERIN.TRLB
aircraft:fuselage:laminar_flow_upper	unitless	define percent laminar flow for fuselage upper surface	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: AERIN.TRUB
aircraft:fuselage:length	ft	Define the Fuselage total length. If total_length is not input for a passenger transport, FLOPS will calculate the fuselage length, width and depth and the length of the passenger compartment.	False	0.0	<class 'float'>	False	GASP: INGASP.ELF<br />FLOPS: WTIN.XL
aircraft:fuselage:length_to_diameter	unitless	fuselage length to diameter ratio	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:fuselage:lift_coefficient_ratio_body_to_wing	unitless	lift coefficient of body over lift coefficient of wing ratio	False	0.0	<class 'float'>	False	GASP: INGASP.CLBqCLW<br />FLOPS: None
aircraft:fuselage:lift_curve_slope_mach0	1/rad	lift curve slope of fuselage at Mach 0	False	0.0	<class 'float'>	False	GASP: INGASP.CLALPH_B0<br />FLOPS: None
aircraft:fuselage:mass	lbm	Fuselage group mass. Contains basic structure and secondary structures such as enclosures, flooring, doors, ramps, panels, etc.	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:fuselage:mass_coefficient	unitless	mass trend coefficient of fuselage	False	136.0	<class 'float'>	False	GASP: INGASP.SKB<br />FLOPS: None
aircraft:fuselage:mass_scaler	unitless	mass scaler of the fuselage structure	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.FRFU
aircraft:fuselage:max_height	ft	maximum fuselage height	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.DF
aircraft:fuselage:max_width	ft	maximum fuselage width	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.WF
aircraft:fuselage:military_cargo_floor	unitless	indicate whether or not there is a military cargo aircraft floor	True	False	<class 'bool'>	False	GASP: None<br />FLOPS: WTIN.CARGF
aircraft:fuselage:nose_fineness	unitless	length to diameter ratio of nose cone	False	1.0	<class 'float'>	False	GASP: INGASP.ELODN<br />FLOPS: None
aircraft:fuselage:num_aisles	unitless	number of aisles in the passenger cabin	True	1	<class 'int'>	False	GASP: INGASP.AS<br />FLOPS: None
aircraft:fuselage:num_fuselages	unitless	number of fuselages	True	1	<class 'int'>	False	GASP: None<br />FLOPS: WTIN.NFUSE
aircraft:fuselage:passenger_compartment_length	ft	length of passenger compartment	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.XLP
aircraft:fuselage:pilot_compartment_length	ft	length of the pilot compartment	False	0.0	<class 'float'>	False	GASP: INGASP.ELPC<br />FLOPS: None
aircraft:fuselage:planform_area	ft**2	fuselage planform area	False	0.0	<class 'float'>	False	GASP: SPF_BODY<br />FLOPS: None
aircraft:fuselage:pressure_differential	psi	fuselage pressure differential during cruise	False	0.0	<class 'float'>	False	GASP: INGASP.DELP<br />FLOPS: None
aircraft:fuselage:pressurized_width_additional	ft	additional pressurized fuselage width for cargo bay	False	0.0	<class 'float'>	False	GASP: INGASP.WPRFUS<br />FLOPS: None
aircraft:fuselage:ref_diameter	ft	A coarse average diameter calculated using the mean of max width and depth.	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: ['EDETIN.XD']
aircraft:fuselage:seat_width	inch	width of the economy class seats	True	0.0	<class 'float'>	False	GASP: INGASP.WS<br />FLOPS: None
aircraft:fuselage:sidebody_thickness_to_chord	unitless	fuselage thickness/chord ratio at side of body	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.TCSOB<br />LEAPS1: None
aircraft:fuselage:simple_layout	unitless	carry out simple or detailed layout of fuselage (for FLOPS based geometry).	True	True	<class 'bool'>	False	GASP: None<br />FLOPS: None
aircraft:fuselage:tail_fineness	unitless	length to diameter ratio of tail cone	False	1.0	<class 'float'>	False	GASP: INGASP.ELODT<br />FLOPS: None
aircraft:fuselage:wetted_area	ft**2	fuselage wetted area	False	0.0	<class 'float'>	False	GASP: INGASP.SF<br />FLOPS: None
aircraft:fuselage:wetted_area_ratio_aftbody_to_total	unitless	aftbody wetted area to total body wetted area	False	0.0	<class 'float'>	False	GASP: INGASP.SAFTqS<br />FLOPS: None
aircraft:fuselage:wetted_area_scaler	unitless	fuselage wetted area scaler	False	1.0	<class 'float'>	False	GASP: INGASP.SF_FAC<br />FLOPS: AERIN.SWETF
aircraft:horizontal_tail:area	ft**2	horizontal tail theoretical area; overridden by vol_coeff, if vol_coeff > 0.0	False	0.0	<class 'float'>	False	GASP: INGASP.SHT<br />FLOPS: WTIN.SHT
aircraft:horizontal_tail:aspect_ratio	unitless	horizontal tail theoretical aspect ratio	False	0.0	<class 'float'>	False	GASP: INGASP.ARHT<br />FLOPS: WTIN.ARHT
aircraft:horizontal_tail:average_chord	ft	mean aerodynamic chord of horizontal tail	False	0.0	<class 'float'>	False	GASP: INGASP.CBARHT<br />FLOPS: None
aircraft:horizontal_tail:characteristic_length	ft	Reynolds characteristic length for the horizontal tail	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:horizontal_tail:drag_factor	unitless	horizontal tail aero calibration factor (including technology factor INGASP.FCFHTT)	False	1.0	<class 'float'>	False	GASP: INGASP.FCFHTC<br />FLOPS: None
aircraft:horizontal_tail:fineness	unitless	horizontal tail fineness ratio	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:horizontal_tail:form_factor	unitless	horizontal tail form factor	False	0.0	<class 'float'>	False	GASP: INGASP.CKHT<br />FLOPS: None
aircraft:horizontal_tail:laminar_flow_lower	unitless	define percent laminar flow for horizontal tail lower surface	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: AERIN.TRLH
aircraft:horizontal_tail:laminar_flow_upper	unitless	define percent laminar flow for horizontal tail upper surface	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: AERIN.TRUH
aircraft:horizontal_tail:mass	lbm	mass of horizontal tail	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:horizontal_tail:mass_coefficient	unitless	mass trend coefficient of horizontal tail	False	0.0	<class 'float'>	False	GASP: INGASP.SKY<br />FLOPS: None
aircraft:horizontal_tail:mass_scaler	unitless	mass scaler of the horizontal tail structure	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.FRHT
aircraft:horizontal_tail:moment_arm	ft	moment arm of horizontal tail	False	0.0	<class 'float'>	False	GASP: INGASP.ELTH<br />FLOPS: None
aircraft:horizontal_tail:moment_ratio	unitless	Ratio of wing chord to horizontal tail moment arm	False	0.0	<class 'float'>	False	GASP: INGASP.COELTH<br />FLOPS: None
aircraft:horizontal_tail:num_tails	unitless	number of horizontal tails	True	1	<class 'int'>	False	GASP: None<br />FLOPS: None
aircraft:horizontal_tail:root_chord	ft	horizontal tail root chord	False	0.0	<class 'float'>	False	GASP: INGASP.CRCLHT<br />FLOPS: None
aircraft:horizontal_tail:span	ft	span of horizontal tail	False	0.0	<class 'float'>	False	GASP: INGASP.BHT<br />FLOPS: None
aircraft:horizontal_tail:sweep	deg	quarter-chord sweep of horizontal tail	False	0.0	<class 'float'>	False	GASP: INGASP.DWPQCH<br />FLOPS: WTIN.SWPHT
aircraft:horizontal_tail:taper_ratio	unitless	horizontal tail theoretical taper ratio	False	0.0	<class 'float'>	False	GASP: INGASP.SLMH<br />FLOPS: WTIN.TRHT
aircraft:horizontal_tail:thickness_to_chord	unitless	horizontal tail thickness-chord ratio	False	0.0	<class 'float'>	False	GASP: INGASP.TCHT<br />FLOPS: WTIN.TCHT
aircraft:horizontal_tail:vertical_tail_mount_location	unitless	Define the decimal fraction of vertical tail span where horizontal tail is mounted. Defaults: 0.0 == for body mounted (default for transport with all engines on wing); 1.0 == for T tail (default for transport with multiple engines on fuselage)	False	0.0	<class 'float'>	False	GASP: INGASP.SAH<br />FLOPS: WTIN.HHT
aircraft:horizontal_tail:volume_coefficient	unitless	tail volume coefficicient of horizontal tail	False	0.0	<class 'float'>	False	GASP: INGASP.VBARHX<br />FLOPS: None
aircraft:horizontal_tail:wetted_area	ft**2	horizontal tail wetted area	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:horizontal_tail:wetted_area_scaler	unitless	horizontal tail wetted area scaler	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: AERIN.SWETH
aircraft:hydraulics:flight_control_mass_coefficient	unitless	mass trend coefficient of hydraulics for flight control system	False	0.0	<class 'float'>	False	GASP: INGASP.CW(3)<br />FLOPS: None
aircraft:hydraulics:gear_mass_coefficient	unitless	mass trend coefficient of hydraulics for landing gear	False	0.0	<class 'float'>	False	GASP: INGASP.CW(4)<br />FLOPS: None
aircraft:hydraulics:mass	lbm	mass of hydraulic system	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:hydraulics:mass_scaler	unitless	mass scaler of the hydraulic system	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.WHYD
aircraft:hydraulics:system_pressure	psi	hydraulic system pressure	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.HYDPR
aircraft:instruments:mass	lbm	instrument group mass	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:instruments:mass_coefficient	unitless	mass trend coefficient of instruments	False	0.0	<class 'float'>	False	GASP: INGASP.CW(2)<br />FLOPS: None
aircraft:instruments:mass_scaler	unitless	mass scaler of the instrument group	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.WIN
aircraft:landing_gear:drag_coefficient	unitless	landing gear drag coefficient	True	0.0	<class 'float'>	False	FLOPS: TOLIN.CDGEAR<br />GASP: None
aircraft:landing_gear:fixed_gear	unitless	Type of landing gear. In GASP, 0 is retractable and 1 is fixed. Here, false is retractable and true is fixed.	True	True	<class 'bool'>	False	GASP: INGASP.IGEAR<br />FLOPS: None
aircraft:landing_gear:main_gear_location	unitless	span fraction of main gear on wing (0=on fuselage, 1=at tip)	False	0.0	<class 'float'>	False	GASP: INGASP.YMG<br />FLOPS: None
aircraft:landing_gear:main_gear_mass	lbm	mass of main landing gear (WMG in GASP)	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:landing_gear:main_gear_mass_fraction	unitless	fraction of total landing gear mass that is main gear mass	False	0.0	<class 'float'>	False	GASP: INGASP.SKMG<br />FLOPS: None
aircraft:landing_gear:main_gear_mass_scaler	unitless	mass scaler of the main landing gear structure	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.FRLGM
aircraft:landing_gear:main_gear_oleo_length	inch	length of extended main landing gear oleo	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.XMLG
aircraft:landing_gear:mass_coefficient	unitless	mass trend coefficient of landing gear	False	0.0	<class 'float'>	False	GASP: INGASP.SKLG<br />FLOPS: None
aircraft:landing_gear:nose_gear_mass	lbm	mass of nose landing gear	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:landing_gear:nose_gear_mass_scaler	unitless	mass scaler of the nose landing gear structure	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.FRLGN
aircraft:landing_gear:nose_gear_oleo_length	inch	length of extended nose landing gear oleo	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.XNLG
aircraft:landing_gear:tail_hook_mass_scaler	unitless	factor on tail mass for arresting hook	False	1.0	<class 'float'>	False	GASP: INGASP.SKTL<br />FLOPS: None
aircraft:landing_gear:total_mass	lbm	total mass of landing gear	False	0.0	<class 'float'>	False	GASP: INGASP.WLG<br />FLOPS: None
aircraft:landing_gear:total_mass_scaler	unitless	technology factor on landing gear mass	False	1.0	<class 'float'>	False	GASP: INGASP.CK12<br />FLOPS: None
aircraft:nacelle:avg_diameter	ft	Average diameter of engine nacelles for each engine model	False	0.0	<class 'float'>	True	GASP: INGASP.DBARN<br />FLOPS: WTIN.DNAC
aircraft:nacelle:avg_length	ft	Average length of nacelles for each engine model	False	0.0	<class 'float'>	True	GASP: INGASP.ELN<br />FLOPS: WTIN.XNAC
aircraft:nacelle:characteristic_length	ft	Reynolds characteristic length for nacelle for each engine model	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
aircraft:nacelle:clearance_ratio	unitless	the minimum number of nacelle diameters above the ground that the bottom of the nacelle must be	False	0.0	<class 'float'>	True	GASP: INGASP.CLEARqDN<br />FLOPS: None
aircraft:nacelle:core_diameter_ratio	unitless	ratio of nacelle diameter to engine core diameter	False	1.25	<class 'float'>	True	GASP: INGASP.DNQDE<br />FLOPS: None
aircraft:nacelle:drag_factor	unitless	nacelle aero calibration factor (including technology factor INGASP.FCFNT)	False	1.0	<class 'float'>	False	GASP: INGASP.FCFNC<br />FLOPS: None
aircraft:nacelle:fineness	unitless	nacelle fineness ratio	False	0.0	<class 'float'>	True	GASP: INGASP.XLQDE<br />FLOPS: None
aircraft:nacelle:form_factor	unitless	nacelle form factor	False	0.0	<class 'float'>	True	GASP: INGASP.CKN<br />FLOPS: None
aircraft:nacelle:laminar_flow_lower	unitless	define percent laminar flow for nacelle lower surface for each engine model	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: AERIN.TRLN
aircraft:nacelle:laminar_flow_upper	unitless	define percent laminar flow for nacelle upper surface for each engine model	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: AERIN.TRUN
aircraft:nacelle:mass	lbm	estimated mass of a single nacelle for each engine model	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
aircraft:nacelle:mass_scaler	unitless	mass scaler of the nacelle structure for each engine model	False	1.0	<class 'float'>	True	GASP: None<br />FLOPS: WTIN.FRNA
aircraft:nacelle:mass_specific	lbm/ft**2	nacelle mass/nacelle surface area; lbm per sq ft.	False	0.0	<class 'float'>	True	GASP: INGASP.UWNAC<br />FLOPS: None
aircraft:nacelle:percent_diam_buried_in_fuselage	unitless	percentage of nacelle diameter buried in fuselage over nacelle diameter	False	0.0	<class 'float'>	True	GASP: INGASP.HEBQDN<br />FLOPS: None
aircraft:nacelle:pylon_drag_factor	unitless	pylon aero calibration factor	False	1.0	<class 'float'>	False	GASP: INGASP.FPYLND<br />FLOPS: None
aircraft:nacelle:surface_area	ft**2	surface area of the outside of one entire nacelle, not just the wetted area	False	0.0	<class 'float'>	True	GASP: INGASP.SN<br />FLOPS: None
aircraft:nacelle:total_wetted_area	ft**2	total nacelles wetted area	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
aircraft:nacelle:wetted_area	ft**2	wetted area of a single nacelle for each engine model	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
aircraft:nacelle:wetted_area_scaler	unitless	nacelle wetted area scaler for each engine model	False	1.0	<class 'float'>	True	GASP: None<br />FLOPS: AERIN.SWETN
aircraft:oxygen_system:mass	lbm	Mass of passenger oxygen system	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:oxygen_system:mass_scaler	unitless	Mass Scaler for the Passenger Oxygen System	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:paint:mass	lbm	mass of paint for all wetted area	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:paint:mass_per_unit_area	lbm/ft**2	mass of paint per unit area for all wetted area	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.WPAINT
aircraft:propulsion:energy_system_mass	lbm	Energy system mass. Contains mass for energy storage and transmission, including the fuel system, battery, and electric powertrain.	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:propulsion:engine_oil_mass_scaler	unitless	Scaler for engine oil mass	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.WOIL
aircraft:propulsion:engine_position_factor	unitless	engine position factor	False	0.0	<class 'float'>	False	GASP: INGASP.SKEPOS<br />FLOPS: None
aircraft:propulsion:mass	lbm	Propulsion group mass. Total mass of all engines on the aircraft, as well as energy system mass.	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:propulsion:misc_mass_scaler	unitless	scaler applied to miscellaneous engine mass (in FLOPS, sum of engine control, starter, and additional mass. In GASP, applied to ADDITIONAL_MASS, which is engine installation mass)	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.WPMSC
aircraft:propulsion:total_engine_controls_mass	lbm	total estimated mass of the engine controls for all engines on aircraft	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:propulsion:total_engine_mass	lbm	total mass of all engines on aircraft	False	0.0	<class 'float'>	False	GASP: INGASP.WEP<br />FLOPS: None
aircraft:propulsion:total_engine_oil_mass	lbm	engine oil mass	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:propulsion:total_engine_pod_mass	lbm	total engine pod mass for all engines on aircraft	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:propulsion:total_misc_mass	lbm	sum of engine control, starter, and additional mass for all engines on aircraft	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:propulsion:total_num_engines	unitless	total number of engines for the aircraft (fuselage, wing, or otherwise)	True	0	<class 'int'>	False	GASP: None<br />FLOPS: None
aircraft:propulsion:total_num_fuselage_engines	unitless	total number of fuselage-mounted engines for the aircraft	True	0	<class 'int'>	False	GASP: None<br />FLOPS: None
aircraft:propulsion:total_num_wing_engines	unitless	total number of wing-mounted engines for the aircraft	True	0	<class 'int'>	False	GASP: None<br />FLOPS: None
aircraft:propulsion:total_reference_sls_thrust	lbf	total maximum thrust of all unscalsed engines on aircraft, sea-level static	True	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:propulsion:total_scaled_sls_thrust	lbf	total maximum thrust of all scaled engines on aircraft, sea-level static	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:propulsion:total_starter_mass	lbm	total mass of starters for all engines on aircraft	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:propulsion:total_thrust_reversers_mass	lbm	total mass of thrust reversers for all engines on aircraft	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:strut:area	ft**2	strut area	False	0.0	<class 'float'>	False	GASP: INGASP.STRTWS<br />FLOPS: None
aircraft:strut:area_ratio	unitless	ratio of strut area to wing area	False	0.0	<class 'float'>	False	GASP: INGASP.SSTQSW<br />FLOPS: None
aircraft:strut:attachment_location	ft	attachment location of strut the full attachment-to-attachment span	False	0.0	<class 'float'>	False	GASP: ['INGASP.STRUT', 'INGASP.STRUTX', 'INGASP.XSTRUT']<br />FLOPS: None
aircraft:strut:attachment_location_dimensionless	unitless	attachment location of strut as fraction of the half-span	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:strut:chord	ft	chord of the strut	False	0.0	<class 'float'>	False	GASP: INGASP.STRTCHD<br />FLOPS: None
aircraft:strut:dimensional_location_specified	unitless	if true the location of the strut is given dimensionally, otherwise it is given non-dimensionally. In GASP this depended on STRUT	True	True	<class 'bool'>	False	GASP: None<br />FLOPS: None
aircraft:strut:drag_factor	unitless	strut aero calibration factor (including technology factor INGASP.FCFSTRT)	False	1.0	<class 'float'>	False	GASP: INGASP.FCFSTRC<br />FLOPS: None
aircraft:strut:fuselage_interference_factor	unitless	strut/fuselage interference factor	False	0.0	<class 'float'>	False	GASP: INGASP.CKSTRT<br />FLOPS: None
aircraft:strut:length	ft	length of the strut	False	0.0	<class 'float'>	False	GASP: INGASP.STRTLNG<br />FLOPS: None
aircraft:strut:mass	lbm	mass of the strut	False	0.0	<class 'float'>	False	GASP: INGASP.WSTRUT<br />FLOPS: None
aircraft:strut:mass_coefficient	unitless	mass trend coefficient of the strut	False	0.0	<class 'float'>	False	GASP: INGASP.SKSTRUT<br />FLOPS: None
aircraft:strut:thickness_to_chord	unitless	thickness to chord ratio of the strut	False	0.0	<class 'float'>	False	GASP: INGASP.TCSTRT<br />FLOPS: None
aircraft:tail_boom:length	ft	cabin length for the tail boom fuselage	False	0.0	<class 'float'>	False	GASP: INGASP.ELFFC<br />FLOPS: None
aircraft:vertical_tail:area	ft**2	vertical tail theoretical area (per tail); overridden by vol_coeff if vol_coeff > 0.0	False	0.0	<class 'float'>	False	GASP: INGASP.SVT<br />FLOPS: WTIN.SVT
aircraft:vertical_tail:aspect_ratio	unitless	vertical tail theoretical aspect ratio	False	0.0	<class 'float'>	False	GASP: INGASP.ARVT<br />FLOPS: WTIN.ARVT
aircraft:vertical_tail:average_chord	ft	mean aerodynamic chord of vertical tail	False	0.0	<class 'float'>	False	GASP: INGASP.CBARVT<br />FLOPS: None
aircraft:vertical_tail:characteristic_length	ft	Reynolds characteristic length for the vertical tail	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:vertical_tail:drag_factor	unitless	vertical tail aero calibration factor (including technology factor INGASP.FCFVTT)	False	1.0	<class 'float'>	False	GASP: INGASP.FCFVTC<br />FLOPS: None
aircraft:vertical_tail:fineness	unitless	vertical tail fineness ratio	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:vertical_tail:form_factor	unitless	vertical tail form factor	False	0.0	<class 'float'>	False	GASP: INGASP.CKVT<br />FLOPS: None
aircraft:vertical_tail:laminar_flow_lower	unitless	define percent laminar flow for vertical tail lower surface	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: AERIN.TRLV
aircraft:vertical_tail:laminar_flow_upper	unitless	define percent laminar flow for vertical tail upper surface	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: AERIN.TRUV
aircraft:vertical_tail:mass	lbm	mass of vertical tail	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:vertical_tail:mass_coefficient	unitless	mass trend coefficient of the vertical tail	False	0.0	<class 'float'>	False	GASP: INGASP.SKZ<br />FLOPS: None
aircraft:vertical_tail:mass_scaler	unitless	mass scaler of the vertical tail structure	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.FRVT
aircraft:vertical_tail:moment_arm	ft	moment arm of vertical tail	False	0.0	<class 'float'>	False	GASP: INGASP.ELTV<br />FLOPS: None
aircraft:vertical_tail:moment_ratio	unitless	ratio of wing span to vertical tail moment arm	False	0.0	<class 'float'>	False	GASP: INGASP.BOELTV<br />FLOPS: None
aircraft:vertical_tail:num_tails	unitless	number of vertical tails	True	1	<class 'int'>	False	GASP: None<br />FLOPS: WTIN.NVERT
aircraft:vertical_tail:root_chord	ft	root chord of vertical tail	False	0.0	<class 'float'>	False	GASP: INGASP.CRCLVT<br />FLOPS: None
aircraft:vertical_tail:span	ft	span of vertical tail	False	0.0	<class 'float'>	False	GASP: INGASP.BVT<br />FLOPS: None
aircraft:vertical_tail:sweep	deg	quarter-chord sweep of vertical tail	False	0.0	<class 'float'>	False	GASP: INGASP.DWPQCV<br />FLOPS: WTIN.SWPVT
aircraft:vertical_tail:taper_ratio	unitless	vertical tail theoretical taper ratio	False	0.0	<class 'float'>	False	GASP: INGASP.SLMV<br />FLOPS: WTIN.TRVT
aircraft:vertical_tail:thickness_to_chord	unitless	vertical tail thickness-chord ratio	False	0.0	<class 'float'>	False	GASP: INGASP.TCVT<br />FLOPS: WTIN.TCVT
aircraft:vertical_tail:volume_coefficient	unitless	tail volume coefficient of the vertical tail	False	0.0	<class 'float'>	False	GASP: INGASP.VBARVX<br />FLOPS: None
aircraft:vertical_tail:wetted_area	ft**2	vertical tails wetted area	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:vertical_tail:wetted_area_scaler	unitless	vertical tail wetted area scaler	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: AERIN.SWETV
aircraft:wing:aeroelastic_tailoring_factor	unitless	Define the decimal fraction of amount of aeroelastic tailoring used in design of wing where: 0.0 == no aeroelastic tailoring; 1.0 == maximum aeroelastic tailoring.	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.FAERT
aircraft:wing:airfoil_technology	unitless	Airfoil technology parameter. Limiting values are: 1.0 represents conventional technology wing (Default); 2.0 represents advanced technology wing.	True	1.0	<class 'float'>	False	GASP: None<br />FLOPS: AERIN.AITEK
aircraft:wing:area	ft**2	reference wing area	False	0.0	<class 'float'>	False	GASP: INGASP.SW<br />FLOPS: CONFIN.SW
aircraft:wing:aspect_ratio	unitless	ratio of the wing span to its mean chord	False	0.0	<class 'float'>	False	GASP: INGASP.AR<br />FLOPS: CONFIN.AR
aircraft:wing:aspect_ratio_reference	unitless	Reference aspect ratio, used for detailed wing mass estimation.	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.ARREF
aircraft:wing:average_chord	ft	mean aerodynamic chord of the wing	False	0.0	<class 'float'>	False	GASP: INGASP.CBARW<br />FLOPS: None
aircraft:wing:bending_material_factor	unitless	Wing bending material factor with sweep adjustment. Used to compute Aircraft.Wing.BENDING_MATERIAL_MASS	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:wing:bending_material_mass	lbm	wing mass breakdown term 1	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:wing:bending_material_mass_scaler	unitless	mass scaler of the bending wing mass term	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.FRWI1
aircraft:wing:bwb_aftbody_mass	lbm	wing mass breakdown term 4	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:wing:bwb_aftbody_mass_scaler	unitless	mass scaler of the blended-wing-body aft-body wing mass term	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.FRWI4
aircraft:wing:center_chord	ft	wing chord at fuselage centerline, usually called root chord	False	0.0	<class 'float'>	False	GASP: INGASP.CRCLW<br />FLOPS: None
aircraft:wing:center_distance	unitless	distance (percent fuselage length) from nose to the wing aerodynamic center	False	0.0	<class 'float'>	False	GASP: INGASP.XWQLF<br />FLOPS: None
aircraft:wing:characteristic_length	ft	Reynolds characteristic length for the wing	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:wing:choose_fold_location	unitless	if true, fold location is based on your chosen value, otherwise it is based on strut location. In GASP this depended on STRUT or YWFOLD	True	True	<class 'bool'>	False	GASP: None<br />FLOPS: None
aircraft:wing:chord_per_semispan_distribution	unitless	chord lengths as fractions of semispan at station locations; overwrites station_chord_lengths	False	[0.0]	<class 'float'>	True	GASP: None<br />FLOPS: WTIN.CHD
aircraft:wing:composite_fraction	unitless	Define the decimal fraction of amount of composites used in wing structure where: 0.0 == no composites; 1.0 == maximum use of composites, approximately equivalent bending_mat_weight=.6, struct_weights=.83, misc_weight=.7 (not necessarily all composite).	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.FCOMP
aircraft:wing:control_surface_area	ft**2	area of wing control surfaces	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:wing:control_surface_area_ratio	unitless	Defines the ratio of total moveable wing control surface areas (flaps, elevators, spoilers, etc.) to reference wing area.	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.FLAPR
aircraft:wing:detailed_wing	unitless	Flag that sets if FLOPS mass should use the detailed wing model	True	False	<class 'bool'>	False	GASP: None<br />FLOPS: None
aircraft:wing:dihedral	deg	wing dihedral (positive) or anhedral (negative) angle	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.DIH
aircraft:wing:drag_factor	unitless	wing aero calibration factor (including technology factor INGASP.FCFWT)	False	1.0	<class 'float'>	False	GASP: INGASP.FCFWC<br />FLOPS: None
aircraft:wing:eng_pod_inertia_factor	unitless	Engine inertia relief factor for wingspan inboard of engine locations. Used to compute Aircraft.Wing.BENDING_MATERIAL_MASS	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:wing:exposed_area	ft**2	exposed wing area, i.e. wing area outside the fuselage, True for both Tube&Wing and HWB	False	0.0	<class 'float'>	False	GASP: SW_EXP<br />FLOPS: None
aircraft:wing:fineness	unitless	wing fineness ratio	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:wing:flap_chord_ratio	unitless	ratio of flap chord to wing chord	False	0.0	<class 'float'>	False	GASP: INGASP.CFOC<br />FLOPS: None
aircraft:wing:flap_deflection_landing	deg	Deflection of flaps for landing	False	40.0	<class 'float'>	False	GASP: INGASP.DFLPLD<br />FLOPS: None
aircraft:wing:flap_deflection_takeoff	deg	Deflection of flaps for takeoff	False	10.0	<class 'float'>	False	GASP: INGASP.DFLPTO<br />FLOPS: None
aircraft:wing:flap_drag_increment_optimum	unitless	drag coefficient increment due to optimally deflected trailing edge flaps (default depends on flap type)	False	0.0	<class 'float'>	False	GASP: INGASP.DCDOTE<br />FLOPS: None
aircraft:wing:flap_lift_increment_optimum	unitless	lift coefficient increment due to optimally deflected trailing edge flaps (default depends on flap type)	False	0.0	<class 'float'>	False	GASP: INGASP.DCLMTE<br />FLOPS: None
aircraft:wing:flap_span_ratio	unitless	fraction of wing trailing edge with flaps	False	0.65	<class 'float'>	False	GASP: INGASP.BTEOB<br />FLOPS: None
aircraft:wing:flap_type	unitless	Set the flap type. Available choices are: plain, split, single_slotted, double_slotted, triple_slotted, fowler, and double_slotted_fowler. In GASP this was JFLTYP and was provided as an int from 1-7	True	FlapType.DOUBLE_SLOTTED	(FlapType.PLAIN, FlapType.SPLIT, FlapType.SINGLE_SLOTTED, FlapType.DOUBLE_SLOTTED, FlapType.TRIPLE_SLOTTED, FlapType.FOWLER, FlapType.DOUBLE_SLOTTED_FOWLER)	True	GASP: INGASP.JFLTYP<br />FLOPS: None
aircraft:wing:fold_dimensional_location_specified	unitless	if true, fold location from the chosen input is an actual fold span, if false it is normalized to the half span. In GASP this depended on STRUT or YWFOLD	True	False	<class 'bool'>	False	GASP: None<br />FLOPS: None
aircraft:wing:fold_mass	lbm	mass of the folding area of the wing	False	0.0	<class 'float'>	False	GASP: INGASP.WWFOLD<br />FLOPS: None
aircraft:wing:fold_mass_coefficient	unitless	mass trend coefficient of the wing fold	False	0.0	<class 'float'>	False	GASP: INGASP.SKWFOLD<br />FLOPS: None
aircraft:wing:folded_span	ft	folded wingspan	False	0.0	<class 'float'>	False	GASP: INGASP.YWFOLD<br />FLOPS: None
aircraft:wing:folded_span_dimensionless	unitless	folded wingspan	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:wing:folding_area	ft**2	wing area of folding part of wings	False	0.0	<class 'float'>	False	GASP: INGASP.SWFOLD<br />FLOPS: None
aircraft:wing:form_factor	unitless	wing form factor	False	0.0	<class 'float'>	False	GASP: INGASP.CKW<br />FLOPS: None
aircraft:wing:fuselage_interference_factor	unitless	wing/fuselage interference factor	False	0.0	<class 'float'>	False	GASP: INGASP.CKI<br />FLOPS: None
aircraft:wing:glove_and_bat	ft**2	total glove and bat area beyond theoretical wing	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.GLOV
aircraft:wing:has_fold	unitless	if true a fold will be included in the wing	True	False	<class 'bool'>	False	GASP: None<br />FLOPS: None
aircraft:wing:has_strut	unitless	if true then aircraft has a strut. In GASP this depended on STRUT	True	False	<class 'bool'>	False	GASP: None<br />FLOPS: None
aircraft:wing:height	ft	wing height above ground during ground run, measured at roughly location of mean aerodynamic chord at the mid plane of the wing	False	0.0	<class 'float'>	False	GASP: INGASP.HTG<br />FLOPS: None
aircraft:wing:high_lift_mass	lbm	mass of the high lift devices	False	0.0	<class 'float'>	False	GASP: INGASP.WHLDEV<br />FLOPS: None
aircraft:wing:high_lift_mass_coefficient	unitless	mass trend coefficient of high lift devices (default depends on flap type)	False	0.0	<class 'float'>	False	GASP: INGASP.WCFLAP<br />FLOPS: None
aircraft:wing:incidence	deg	incidence angle of the wings with respect to the fuselage	False	0.0	<class 'float'>	False	GASP: INGASP.EYEW<br />FLOPS: None
aircraft:wing:input_station_distribution	unitless	wing station locations as fractions of semispan; overwrites station_locations	True	[0.0]	<class 'float'>	True	GASP: None<br />FLOPS: WTIN.ETAW
aircraft:wing:laminar_flow_lower	unitless	define percent laminar flow for wing lower surface	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: AERIN.TRLW
aircraft:wing:laminar_flow_upper	unitless	define percent laminar flow for wing upper surface	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: AERIN.TRUW
aircraft:wing:leading_edge_sweep	rad	sweep angle at leading edge of wing	False	0.0	<class 'float'>	False	GASP: INGASP.SWPLE<br />FLOPS: None
aircraft:wing:load_distribution_control	unitless	controls spatial distribution of integration stations for detailed wing, in [1, 3]	True	2.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.PDIST
aircraft:wing:load_fraction	unitless	fraction of load carried by defined wing	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.PCTL
aircraft:wing:load_path_sweep_distribution	deg	Define the sweep of load path at station locations. Typically parallel to rear spar tending toward max t/c of airfoil. The Ith value is used between wing stations I and I+1.	False	[0.0]	<class 'float'>	True	GASP: None<br />FLOPS: WTIN.SWL
aircraft:wing:loading_above_20	unitless	if true the wing loading is stated to be above 20 psf. In GASP this depended on WGS	True	True	<class 'bool'>	False	GASP: None<br />FLOPS: None
aircraft:wing:mass	lbm	Wing group mass. Contains basic & secondary structures, ailerons/elevons, spoilers, flaps, and slats.	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:wing:mass_coefficient	unitless	mass trend coefficient of the wing without high lift devices	False	0.0	<class 'float'>	False	GASP: INGASP.SKWW<br />FLOPS: None
aircraft:wing:mass_scaler	unitless	mass scaler of the overall wing	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.FRWI
aircraft:wing:material_factor	unitless	correction factor for the use of non optimum material	False	0.0	<class 'float'>	False	GASP: INGASP.SKNO<br />FLOPS: None
aircraft:wing:max_camber_at_70_semispan	unitless	Maximum camber at 70 percent semispan, percent of local chord	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: AERIN.CAM
aircraft:wing:max_lift_ref	unitless	input reference maximum lift coefficient for basic wing	False	0.0	<class 'float'>	False	GASP: INGASP.RCLMAX<br />FLOPS: None
aircraft:wing:max_slat_deflection_landing	deg	leading edge slat deflection during landing	False	10.0	<class 'float'>	False	GASP: INGASP.DELLED<br />FLOPS: None
aircraft:wing:max_slat_deflection_takeoff	deg	leading edge slat deflection during takeoff	False	10.0	<class 'float'>	False	GASP: INGASP.DELLED<br />FLOPS: None
aircraft:wing:max_thickness_location	unitless	location (percent chord) of max wing thickness	False	0.0	<class 'float'>	False	GASP: INGASP.XCTCMX<br />FLOPS: None
aircraft:wing:min_pressure_location	unitless	location (percent chord) of peak suction	False	0.0	<class 'float'>	False	GASP: INGASP.XCPS<br />FLOPS: None
aircraft:wing:misc_mass	lbm	wing mass breakdown term 3	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:wing:misc_mass_scaler	unitless	mass scaler of the miscellaneous wing mass term	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.FRWI3
aircraft:wing:num_flap_segments	unitless	number of flap segments per wing panel	True	2	<class 'int'>	False	GASP: INGASP.FLAPN<br />FLOPS: None
aircraft:wing:num_integration_stations	unitless	number of integration stations	True	50	<class 'int'>	False	GASP: None<br />FLOPS: WTIN.NSTD
aircraft:wing:optimum_flap_deflection	deg	optimum flap deflection angle (default depends on flap type)	False	0.0	<class 'float'>	False	GASP: INGASP.DELTEO<br />FLOPS: None
aircraft:wing:optimum_slat_deflection	deg	optimum slat deflection angle	False	20.0	<class 'float'>	False	GASP: INGASP.DELLEO<br />FLOPS: None
aircraft:wing:outboard_semispan	ft	Outboard semispan (used if a detailed wing outboard is being added to a BWB fuselage)	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: FUSEIN.OSSPAN
aircraft:wing:root_chord	ft	wing chord length at at the wing/fuselage intersection	False	0.0	<class 'float'>	False	GASP: INGASP.CROOTW<br />FLOPS: WTIN.XLW
aircraft:wing:shear_control_mass	lbm	wing mass breakdown term 2	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:wing:shear_control_mass_scaler	unitless	mass scaler of the shear and control term	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.FRWI2
aircraft:wing:slat_chord_ratio	unitless	ratio of slat chord to wing chord	False	0.0	<class 'float'>	False	GASP: INGASP.CLEOC<br />FLOPS: None
aircraft:wing:slat_lift_increment_optimum	unitless	lift coefficient increment due to optimally deflected LE slats	False	0.0	<class 'float'>	False	GASP: INGASP.DCLMLE<br />FLOPS: None
aircraft:wing:slat_span_ratio	unitless	fraction of wing leading edge with slats	False	0.0	<class 'float'>	False	GASP: INGASP.BLEOB<br />FLOPS: None
aircraft:wing:span	ft	span of main wing	False	0.0	<class 'float'>	False	GASP: INGASP.B<br />FLOPS: WTIN.SPAN
aircraft:wing:span_efficiency_factor	unitless	coefficient for calculating span efficiency for extreme taper ratios	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: AERIN.E
aircraft:wing:span_efficiency_reduction	unitless	Define a switch for span efficiency reduction for extreme taper ratios: True == a span efficiency factor (*wing_span_efficiency_factor0*) is calculated based on wing taper ratio and aspect ratio; False == a span efficiency factor (*wing_span_efficiency_factor0*) is set to 1.0.	True	False	<class 'bool'>	False	GASP: None<br />FLOPS: AERIN.MIKE
aircraft:wing:strut_bracing_factor	unitless	Define the wing strut-bracing factor where: 0.0 == no wing-strut; 1.0 == full benefit from strut bracing.	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.FSTRT
aircraft:wing:surface_control_mass	lbm	mass of surface controls	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:wing:surface_control_mass_coefficient	unitless	Surface controls weight coefficient	False	0.0	<class 'float'>	False	GASP: INGASP.SKFW<br />FLOPS: None
aircraft:wing:surface_control_mass_scaler	unitless	Surface controls mass scaler	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.FRSC
aircraft:wing:sweep	deg	quarter-chord sweep angle of the wing	False	0.0	<class 'float'>	False	GASP: INGASP.DLMC4<br />FLOPS: CONFIN.SWEEP
aircraft:wing:taper_ratio	unitless	taper ratio of the wing	False	0.0	<class 'float'>	False	GASP: INGASP.SLM<br />FLOPS: CONFIN.TR
aircraft:wing:thickness_to_chord	unitless	wing thickness-chord ratio (weighted average)	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: CONFIN.TCA
aircraft:wing:thickness_to_chord_distribution	unitless	the thickeness-chord ratios at station locations	False	[0.0]	<class 'float'>	True	GASP: None<br />FLOPS: WTIN.TOC
aircraft:wing:thickness_to_chord_reference	unitless	Reference thickness-to-chord ratio, used for detailed wing mass estimation.	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.TCREF
aircraft:wing:thickness_to_chord_root	unitless	thickness-to-chord ratio at the root of the wing	False	0.0	<class 'float'>	False	GASP: INGASP.TCR<br />FLOPS: None
aircraft:wing:thickness_to_chord_tip	unitless	thickness-to-chord ratio at the tip of the wing	False	0.0	<class 'float'>	False	GASP: INGASP.TCT<br />FLOPS: None
aircraft:wing:thickness_to_chord_unweighted	unitless	wing thickness-chord ratio at the wing station of the mean aerodynamic chord	False	0.0	<class 'float'>	False	GASP: INGASP.TC<br />FLOPS: None
aircraft:wing:ultimate_load_factor	unitless	structural ultimate load factor	False	0.0	<class 'float'>	False	GASP: INGASP.ULF<br />FLOPS: WTIN.ULF
aircraft:wing:var_sweep_mass_penalty	unitless	Define the fraction of wing variable sweep mass penalty where: 0.0 == fixed-geometry wing; 1.0 == full variable-sweep wing.	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.VARSWP
aircraft:wing:vertical_mount_location	unitless	vertical wing mount location on fuselage (0 = low wing, 1 = high wing). It is continuous variable between 0 and 1 are acceptable.	False	0.0	<class 'float'>	False	GASP: INGASP.HWING<br />FLOPS: None
aircraft:wing:wetted_area	ft**2	wing wetted area	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
aircraft:wing:wetted_area_scaler	unitless	wing wetted area scaler	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: AERIN.SWETW
aircraft:wing:zero_lift_angle	deg	zero lift angle of attack	False	0.0	<class 'float'>	False	GASP: INGASP.ALPHL0<br />FLOPS: None
density	lbm/ft**3	Atmospheric density at the vehicle's current altitude	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
dynamic_pressure	lbf/ft**2	Atmospheric dynamic pressure at the vehicle's current flight condition	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
dynamic_viscosity	lbf*s/ft**2	Atmospheric dynamic viscosity at the vehicle's current flight condition	False	0.0	<class 'float'>	True	GASP: XKV<br />FLOPS: None
kinematic_viscosity	ft**2/s	Atmospheric kinematic viscosity at the vehicle's current flight condition	False	0.0	<class 'float'>	True	GASP: XKV<br />FLOPS: None
mach	unitless	Current Mach number of the vehicle	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
mach_rate	unitless	Current rate at which the Mach number of the vehicle is changing	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
speed_of_sound	ft/s	Atmospheric speed of sound at vehicle's current flight condition	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
static_pressure	lbf/ft**2	Atmospheric static pressure at the vehicle's current flight condition	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
temperature	degR	Atmospheric temperature at vehicle's current flight condition	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
altitude	ft	Current geometric altitude of the vehicle	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
altitude_rate	ft/s	Current rate of altitude change (climb rate) of the vehicle	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
altitude_rate_max	ft/s	Current maximum possible rate of altitude change (climb rate) of the vehicle (at hypothetical maximum thrust condition)	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
distance	NM	The total distance the vehicle has traveled since brake release at the current time	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: range
distance_rate	NM/s	The rate at which the distance traveled is changing at the current time	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: range_rate
flight_path_angle	rad	Current flight path angle	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
flight_path_angle_rate	rad/s	Current rate at which flight path angle is changing	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
specific_energy	m/s	Rate of change in specific energy (energy per unit weight) of the vehicle at current flight condition	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
specific_energy_rate	m/s	Rate of change in specific energy (specific power) of the vehicle at current flight condition	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
specific_energy_rate_excess	m/s	Specific excess power of the vehicle at current flight condition and at hypothetical maximum thrust	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
velocity	ft/s	Current velocity of the vehicle along its body axis	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
velocity_rate	ft/s**2	Current rate of change in velocity (acceleration) of the vehicle along its body axis	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
angle_of_attack	deg	Angle between aircraft wing cord and relative wind	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
battery_state_of_charge	unitless	battery's current state of charge	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
cumulative_electric_energy_used	kJ	Total amount of electric energy consumed by the vehicle up until this point in the mission	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
drag	lbf	Current total drag experienced by the vehicle	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
drag_coefficient	unitless	Current total drag coefficient experienced by the vehicle	False	1.0	<class 'float'>	True	GASP: None<br />FLOPS: None
lift	lbf	Current total lift produced by the vehicle	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
lift_coefficient	unitless	Current total lift coefficient produced by the vehicle	False	1.0	<class 'float'>	True	GASP: None<br />FLOPS: None
mass	lbm	Current total mass of the vehicle	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
mass_rate	lbm/s	Current rate at which the mass of the vehicle is changing	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
electric_power_in	kW	The electric power consumption of each engine during the mission.	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
electric_power_in_total	kW	Current total electric power consumption of the vehicle	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
fuel_flow_rate	lbm/h	Current rate of fuel consumption of the vehicle, per single instance of each engine model. Consumption (i.e. mass reduction) of fuel is defined as positive.	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
fuel_flow_rate_negative	lbm/h	Current rate of fuel consumption of the vehicle, per single instance of each engine model. Consumption (i.e. mass reduction) of fuel is defined as negative.	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
fuel_flow_rate_negative_total	lbm/h	Current rate of total fuel consumption of the vehicle. Consumption (i.e. mass reduction) of fuel is defined as negative.	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
fuel_flow_rate_total	lbm/h	Current rate of total fuel consumption of the vehicle. Consumption (i.e. mass reduction) of fuel is defined as positive.	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
hybrid_throttle	unitless	Current secondary throttle setting of each individual engine model on the vehicle, used as an additional degree of control for hybrid engines	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
nox_rate	lbm/h	Current rate of nitrous oxide (NOx) production by the vehicle, per single instance of each engine model	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
nox_rate_total	lbm/h	Current total rate of nitrous oxide (NOx) production by the vehicle	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
propeller_tip_speed	ft/s	linear propeller tip speed due to rotation (not airspeed at propeller tip)	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
rotations_per_minute	rpm	Rotational rate of shaft, per engine.	False	0.0	<class 'float'>	True	GASP: ['RPM', 'RPMe']<br />FLOPS: None
shaft_power	hp	current shaft power, per engine	False	0.0	<class 'float'>	True	GASP: ['SHP, EHP']<br />FLOPS: None
shaft_power_max	hp	The maximum possible shaft power currently producible, per engine	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
t4	degR	Current turbine exit temperature (T4) of turbine engines on vehicle, per single instance of each engine model	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
throttle	unitless	Current throttle setting for each individual engine model on the vehicle	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
thrust_net	lbf	Current net thrust produced by engines, per single instance of each engine model	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
thrust_net_max	lbf	Hypothetical maximum possible net thrust that can be produced per single instance of each engine model at the vehicle's current flight condition	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
thrust_net_max_total	lbf	Hypothetical maximum possible net thrust produced by the vehicle at its current flight condition	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
thrust_net_total	lbf	Current total net thrust produced by the vehicle	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
torque	N*m	Current torque being produced, per engine	False	0.0	<class 'float'>	True	GASP: TORQUE<br />FLOPS: None
torque_max	N*m	Hypothetical maximum possible torque being produced at the current flight condition, per engine	False	0.0	<class 'float'>	True	GASP: None<br />FLOPS: None
mission:block_fuel_mass	lbm	Fuel burned from taxi out of the gate through the regular missions to taxi into the gate.This does not include fuel burned in reserve phases. This works for energy-state EOM. Not used in 2DOF EOM	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:final_mass	lbm	The final weight of the vehicle at the end of the last regular_phase (does not include reserve phases).	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:final_time	min	Total mission time from the start of the first regular_phaseto the end of the last regular_phase (does not include reserve phases).	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:fuel_mass	lbm	Fuel burned from taxi-out through all regular phases of the mission (e.g. takeoff, climb, cruse, descent, landing).This does not include fuel burned in reserve phases or taxi-in.The only time taxi-in would be included in this is if the userspecifies a taxi phase as part of the regular mission phases.	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:gravity	m/s**2	Gravitational acceleration of the planet. This model is updatedin preprocess_options() based on which atmosphere is selected.This ensures the gravity model matches the planet.	True	9.80665	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:gross_mass	lbm	Gross takeoff mass of aircraft for the mission being flown.May differ from Aircraft.Design.GROSS_MASS for off-design missions.	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:operating_items_mass	lbm	Operating Items group. Includes crew, unusable fuel, and oil mass.	False	0.0	<class 'float'>	False	GASP: INGASP.WFUL<br />FLOPS: None
mission:operating_items_mass_additional	lbm	Other operating items (e.g. external tanks, life rafts).	False	0.0	<class 'float'>	False	GASP: CW(16)<br />FLOPS: None
mission:operating_mass	lbm	Operating mass of the aircraft. Includes structure mass, crew (and crew baggage), unusable fuel, oil, and operational items like cargo containers and passenger service mass.	False	0.0	<class 'float'>	False	GASP: INGASP.OWE<br />FLOPS: MISSIN.DOWE
mission:range	NM	actual range that the aircraft flies on this mission. Equal to Aircraft.Design.RANGE value in the design case.	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:reserve_fuel_margin	unitless	required fuel reserves: given as a precentage of mission fuel.Mission fuel only includes normal phases and excludes reserve phases.	True	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:reserve_fuel_mass	lbm	fuel burned during reserve phases, this does not include fuel burned in regular phases	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:reserve_fuel_mass_additional	lbm	required fuel reserves: directly in lbm	True	0.0	<class 'float'>	False	GASP: INGASP.FRESF<br />FLOPS: None
mission:sea_level_density	kg/m**3	Atmospheric density at seal level for this planet.	True	1.225	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:total_fuel_mass	lbm	total fuel carried at the beginnning of a mission includes fuel burned in the mission, reserve fuel and fuel margin	False	0.0	<class 'float'>	False	GASP: INGASP.WFA<br />FLOPS: None
mission:total_reserve_fuel_mass	lbm	the total fuel reserves which is the sum of: Mission.RESERVE_FUEL_MASS, Mission.RESERVE_FUEL_MASS_ADDITIONAL, Mission.RESERVE_FUEL_MARGIN	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:zero_fuel_mass	lbm	Aircraft zero fuel mass. Includes operating mass, passengers, baggage, and cargo.	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:constraints:excess_fuel_mass_capacity	lbm	Difference between the usable fuel capacity on the aircraft and the total fuel (including reserve) required for the mission. Must be >= 0 to ensure that the aircraft has enough fuel to complete the mission	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:constraints:gearbox_shaft_power_residual	kW	Must be zero or positive to ensure that the gearbox is sized large enough to handle the maximum shaft power the engine could output during any part of the mission	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:constraints:mass_residual	lbm	residual to make sure aircraft mass closes on actual gross takeoff mass, value should be zero at convergence (within acceptable tolerance)	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:constraints:max_mach	unitless	aircraft cruise Mach number	True	0.0	<class 'float'>	False	GASP: None<br />FLOPS: WTIN.VMMO
mission:constraints:range_residual	NM	residual to make sure aircraft range is equal to the targeted range, value should be zero at convergence (within acceptable tolerance)	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:constraints:range_residual_reserve	NM	residual to make sure aircraft reserve mission range is equal to the targeted range, value should be zero at convergence (within acceptable tolerance)	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:landing:airport_altitude	ft	altitude of airport where aircraft lands	False	0.0	<class 'float'>	False	GASP: INGASP.ALTLND<br />FLOPS: None
mission:landing:braking_delay	s	time delay between touchdown and the application of brakes	False	1.0	<class 'float'>	False	GASP: INGASP.TDELAY<br />FLOPS: None
mission:landing:braking_friction_coefficient	unitless	landing coefficient of friction, with brakes on	False	0.3	<class 'float'>	False	FLOPS: None<br />GASP: INGASP.MUB
mission:landing:drag_coefficient_flap_increment	unitless	drag coefficient increment at landing due to flaps	False	0.0	<class 'float'>	False	GASP: INGASP.DCD<br />FLOPS: None
mission:landing:drag_coefficient_min	unitless	Minimum drag coefficient for takeoff. Typically this is CD at zero lift.	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: TOLIN.CDMLD
mission:landing:field_length	ft	FAR landing field length	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:landing:flare_rate	deg/s	flare rate in detailed landing	False	2.0	<class 'float'>	False	GASP: None<br />FLOPS: TOLIN.VANGLD
mission:landing:glide_to_stall_ratio	unitless	ratio of glide (approach) speed to stall speed	False	1.3	<class 'float'>	False	GASP: INGASP.VRATT<br />FLOPS: None
mission:landing:ground_distance	ft	distance covered over the ground during landing	False	0.0	<class 'float'>	False	GASP: INGASP.DLT<br />FLOPS: None
mission:landing:initial_altitude	ft	altitude where landing calculations begin	False	0.0	<class 'float'>	False	GASP: INGASP.HIN<br />FLOPS: None
mission:landing:initial_mach	unitless	approach Mach number	False	0.1	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:landing:initial_velocity	ft/s	approach velocity	False	0.0	<class 'float'>	False	GASP: VGL<br />FLOPS: None
mission:landing:lift_coefficient_flap_increment	unitless	lift coefficient increment at landing due to flaps	False	0.0	<class 'float'>	False	GASP: INGASP.DCL<br />FLOPS: None
mission:landing:lift_coefficient_max	unitless	maximum lift coefficient for landing	False	0.0	<class 'float'>	False	GASP: INGASP.CLMWLD<br />FLOPS: AERIN.CLLDM
mission:landing:maximum_flare_load_factor	unitless	maximum load factor during landing flare	False	1.15	<class 'float'>	False	GASP: INGASP.XLFMX<br />FLOPS: None
mission:landing:maximum_sink_rate	ft/min	maximum rate of sink during glide	False	1000.0	<class 'float'>	False	GASP: INGASP.RSMX<br />FLOPS: None
mission:landing:obstacle_height	ft	landing obstacle height above the ground at airport altitude	False	50.0	<class 'float'>	False	GASP: INGASP.HAPP<br />FLOPS: None
mission:landing:rolling_friction_coefficient	unitless	coefficient of rolling friction for groundroll portion of takeoff	False	0.025	<class 'float'>	False	FLOPS: None<br />GASP: None
mission:landing:spoiler_drag_coefficient	unitless	drag coefficient for spoilers during landing rollout	False	0.0	<class 'float'>	False	FLOPS: None<br />GASP: None
mission:landing:spoiler_lift_coefficient	unitless	lift coefficient for spoilers during landing rollout	False	0.0	<class 'float'>	False	FLOPS: None<br />GASP: None
mission:landing:stall_velocity	ft/s	stall speed during approach	False	0.0	<class 'float'>	False	GASP: INGASP.VST<br />FLOPS: None
mission:landing:touchdown_mass	lbm	computed mass of aircraft for landing, is only required to be equal to Aircraft.Design.TOUCHDOWN_MASS_MAX when the design case is being run for ENERGY_STATE missions this is the mass at the end of the last regular phase (non-reserve phase)	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:landing:touchdown_sink_rate	ft/s	sink rate at touchdown	False	3.0	<class 'float'>	False	GASP: INGASP.SINKTD<br />FLOPS: None
mission:objectives:fuel	unitless	regularized objective that minimizes total fuel mass subject to other necessary additions	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:objectives:range	unitless	regularized objective that maximizes range subject to other necessary additions	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:takeoff:airport_altitude	ft	altitude of airport where aircraft takes off	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:takeoff:angle_of_attack_runway	deg	angle of attack on ground	True	0.0	<class 'float'>	False	FLOPS: TOLIN.ALPRUN<br />GASP: None
mission:takeoff:ascent_duration	s	duration of the ascent phase of takeoff	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:takeoff:ascent_t_initial	s	time that the ascent phase of takeoff starts at	False	10.0	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:takeoff:braking_friction_coefficient	unitless	takeoff coefficient of friction, with brakes on	False	0.3	<class 'float'>	False	FLOPS: TOLIN.BRAKMU<br />GASP: None
mission:takeoff:climbout_thrust_fraction	unitless	Fraction of Aircraft.Propulsion.TOTAL_SCALED_SLS_THRUST to use forclimbout phase of simple takeoff calculations. For 2 engine aircraft set = 0.5 for one engine out.	False	1.0	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:takeoff:decision_speed_increment	kn	increment of engine failure decision speed above stall speed	False	5.0	<class 'float'>	False	GASP: INGASP.DV1<br />FLOPS: None
mission:takeoff:drag_coefficient_flap_increment	unitless	drag coefficient increment at takeoff due to flaps	False	0.0	<class 'float'>	False	GASP: INGASP.DCD<br />FLOPS: None
mission:takeoff:drag_coefficient_min	unitless	Minimum drag coefficient for takeoff. Typically this is CD at zero lift.	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: TOLIN.CDMTO
mission:takeoff:field_length	ft	FAR takeoff field length	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:takeoff:final_altitude	ft	altitude of aircraft at the end of takeoff	False	35.0	<class 'float'>	False	GASP: None<br />FLOPS: TOLIN.OBSTO
mission:takeoff:final_mach	unitless	Mach number of aircraft after taking off and clearing a 35 foot obstacle	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:takeoff:final_mass	lbm	mass after aircraft has cleared 35 ft obstacle	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:takeoff:final_velocity	m/s	velocity of aircraft after taking off and clearing a 35 foot obstacle	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:takeoff:fuel_mass	lbm	Fuel burned during takeoff for energy-state EOM. Not used in 2DOF EOM.	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: MISSIN.FTKOFL
mission:takeoff:ground_distance	ft	ground distance covered by takeoff with all engines operating	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:takeoff:lift_coefficient_flap_increment	unitless	lift coefficient increment at takeoff due to flaps	False	0.0	<class 'float'>	False	GASP: INGASP.DCL<br />FLOPS: None
mission:takeoff:lift_coefficient_max	unitless	maximum lift coefficient for takeoff	False	2.0	<class 'float'>	False	GASP: INGASP.CLMWTO<br />FLOPS: ['AERIN.CLTOM', 'TOLIN.CLTOM']
mission:takeoff:lift_over_drag	unitless	ratio of lift to drag at takeoff	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:takeoff:obstacle_height	ft	takeoff obstacle height above the ground at airport altitude	True	35.0	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:takeoff:rolling_friction_coefficient	unitless	coefficient of rolling friction for groundroll portion of takeoff	False	0.025	<class 'float'>	False	GASP: INGASP.UM<br />FLOPS: TOLIN.ROLLMU
mission:takeoff:rotation_speed_increment	kn	increment of takeoff rotation speed above engine failure decision speed	False	5.0	<class 'float'>	False	GASP: INGASP.DVR<br />FLOPS: None
mission:takeoff:rotation_velocity	kn	rotation velocity	False	0.0	<class 'float'>	False	GASP: INGASP.VR<br />FLOPS: None
mission:takeoff:spoiler_drag_coefficient	unitless	drag coefficient for spoilers during takeoff abort	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: TOLIN.CDSPOL
mission:takeoff:spoiler_lift_coefficient	unitless	lift coefficient for spoilers during takeoff abort	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: TOLIN.CLSPOL
mission:takeoff:thrust_incidence	deg	thrust incidence on ground	True	0.0	<class 'float'>	False	FLOPS: TOLIN.TINC<br />GASP: None
mission:taxi:duration	h	time spent taxiing before takeoff	True	0.167	<class 'float'>	False	GASP: INGASP.DELTT<br />FLOPS: None
mission:taxi:fuel_mass_taxi_in	lbm	Fuel burned to taxi from the runway to the gate. Can be used with energy-stand and 2DOF EOM.	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:taxi:fuel_mass_taxi_out	lbm	Fuel burned to taxi from the gate to the runway. Only used in energy-state EOM. Not used in 2DOF EOM.	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
mission:taxi:mach	unitless	speed during taxi	False	0.0	<class 'float'>	False	GASP: None<br />FLOPS: None
settings:aerodynamics_method	unitless	Sets which legacy code's methods will be used for aerodynamics estimation	True	None	(FLOPS, GASP)	False	GASP: None<br />FLOPS: None
settings:atmosphere_model	unitless	The atmospheric model used. Chose one of: standard, tropical, polar, hot, cold, mars_reference, mars_hellas_hot, mars_hellas_cold, mars_equator_hot, mars_equator_cold, mars_polar_hot, mars_polar_cold, venus_reference	True	AtmosphereModel.STANDARD	(AtmosphereModel.STANDARD, AtmosphereModel.COLD, AtmosphereModel.HOT, AtmosphereModel.TROPICAL, AtmosphereModel.POLAR, AtmosphereModel.MARS_REFERENCE, AtmosphereModel.MARS_HELLAS_HOT, AtmosphereModel.MARS_HELLAS_COLD, AtmosphereModel.MARS_EQUATOR_HOT, AtmosphereModel.MARS_EQUATOR_COLD, AtmosphereModel.MARS_POLAR_HOT, AtmosphereModel.MARS_POLAR_COLD, AtmosphereModel.VENUS_REFERENCE)	False	GASP: None<br />FLOPS: None
settings:equations_of_motion	unitless	Sets which equations of motion Aviary will use in mission analysis	True	None	(EquationsOfMotion.ENERGY_STATE, EquationsOfMotion.TWO_DEGREES_OF_FREEDOM, EquationsOfMotion.SOLVED_2DOF, EquationsOfMotion.CUSTOM)	False	GASP: None<br />FLOPS: None
settings:mass_method	unitless	Sets which legacy code's methods will be used for mass estimation	True	None	(FLOPS, GASP)	False	GASP: None<br />FLOPS: None
settings:payload_range	unitless	for SIZING missions only. If True, run a set of off-design missions to create a payload range diagram. Assumes SIZING mission describes the max payload + fuel point	True	False	<class 'bool'>	False	GASP: None<br />FLOPS: None
settings:problem_type	unitless	Select from Aviary's built in problem types: SIZING, OFF_DESIGN_MIN_FUEL, OFF_DESIGN_MAX_RANGE and MULTI_MISSION	True	None	(ProblemType.SIZING, ProblemType.OFF_DESIGN_MIN_FUEL, ProblemType.OFF_DESIGN_MAX_RANGE, ProblemType.MULTI_MISSION)	False	GASP: None<br />FLOPS: None
settings:verbosity	unitless	Sets how much information Aviary outputs when run. Options include:0. QUIET: All output except errors are suppressed1. BRIEF: Only important information is output, in human-readable format2. VERBOSE: All user-relevant information is output, in human-readable format3. DEBUG: Any information can be outtputed, including warnings, intermediate calculations, etc., with no formatting requirement	True	1	(0, 1, 2, 3)	False	GASP: None<br />FLOPS: None
aircraft:center_of_gravity	ft	Center of gravity	False	0.0	<class 'float'>	False	NaN
aircraft:wing:flap:area	ft**2	planform area of flap	False	10.0	<class 'float'>	False	NaN
aircraft:wing:flap:root_chord	ft	chord of flap at root of wing	False	1.0	<class 'float'>	False	NaN
aircraft:wing:flap:span	ft	span of flap	False	60.0	<class 'float'>	False	NaN
aircraft:jury:mass	kg	mass of jury strut	False	50.0	<class 'float'>	False	NaN
aircraft:engine:cooling:mass	kg	mass of cooling system for one engine	False	100.0	<class 'float'>	False	NaN
aircraft:wing:winglets	unitless	Tells whether the aircraft has winglets	True	True	<class 'bool'>	False	NaN