def fuselageDiameter(self):
"""
Aircraft Diameter
:Unit: [m]
:rtype: float
"""
return float(Importer(Component='Fuselage',
VariableName='Fuselage Diameter',
Default=4.0,
Path=self.filePath).getValue)
def fuselageLength(self):
"""
Aircraft fuselage length
:Unit: [m]
:rtype: float
"""
return float(Importer(Component='Fuselage',
VariableName='Fuselage Length',
Default=30.0,
Path=self.filePath).getValue)
def tailSlenderness(self):
"""
Aircraft tail slenderness, equal to tail length over fuselage diameter
:Unit: [ ]
:rtype: float
"""
return float(Importer(Component='Fuselage',
VariableName='Tail Slenderness',
Default=2.11,
Path=self.filePath).getValue)
def tailUpAngle(self):
"""
Aircraft tail angle, positive upward
:Unit: [deg]
:rtype: float
"""
return float(Importer(Component='Fuselage',
VariableName='Tail Up Angle',
Default=5.0,
Path=self.filePath).getValue)
def noseWheelRadius(self):
"""
Diameter of the main wheel.
:Unit: [m]
:rtype: float
"""
return float(Importer(Component='Landing Gear',
VariableName='Nose wheel radius',
Default=0.3,
Path=self.filePath).getValue)
def projectName(self):
"""
Name of the project or of the airplane.
:return:
"""
return str(
Importer(Component='Configuration',
VariableName='Aircraft name',
Default='Tail sizing',
Path=self.filePath).getValue)
def percxfoil(self):
"""
Span percentage for xFoil plan, user requested
:Unit: [ ]
:rtype: float
"""
return float(Importer(Component='Htp',
VariableName='Span percentage for xFoil analysis',
Default=.5,
Path=self.filePath).getValue)
def hCruise(self):
"""
Aircraft cruise altitude
:Unit: [m]
:rtype: float
"""
return float(Importer(Component='Performance',
VariableName='Cruise altitude',
Default=10000.,
Path=self.filePath).getValue)
def height(self):
"""
Height of the main landing gear wrt to the belly of the aircraft
:Unit: [m]
:rtype: float
"""
return float(Importer(Component='Landing Gear',
VariableName='Landing gear height',
Default=1.6,
Path=self.filePath).getValue)
def wingLoading(self):
"""
Aircraft wing loading
:Unit: [kg / m^2]
:rtype: float
"""
return float(Importer(Component='Performance',
VariableName='Wing Loading',
Default=5000.,
Path=self.filePath).getValue)
def mTOW(self):
"""
Aircraft maximum take off weight
:Unit: [N]
:rtype: float
"""
return float(Importer(Component='Performance',
VariableName='MTOW',
Default=422713.,
Path=self.filePath).getValue)
def latPos(self):
"""
Lateral gear position with regard to the fuselage diameter
:Unit: []
:rtype: float
"""
return float(Importer(Component='Landing Gear',
VariableName='Lateral gear position',
Default=1.8,
Path=self.filePath).getValue)
def maCruise(self):
"""
Cruise Mach number
:Unit: []
:rtype: float
"""
return float(Importer(Component='Performance',
VariableName='M cruise',
Default=0.77,
Path=self.filePath).getValue)
def fusLongPos(self):
"""
Longitudinal position on fuselage wrt to the nacelle length.
:return:
"""
return float(
Importer(Component='Engine',
VariableName='Engine longitudinal pos on fuselage',
Default=0.2,
Path=self.filePath).getValue)
def fusVertPos(self):
"""
Vertical position on fuselage wrt to the fuselage diameter.
:return:
"""
return float(
Importer(Component='Engine',
VariableName='Engine vertical pos on fuselage',
Default=0.01,
Path=self.filePath).getValue)
def etaMech(self):
"""
Mechanical efficiency of engine
:Unit: [ ]
:rtype: float
"""
return float(
Importer(Component='Engine',
VariableName='Mechanical efficiency',
Default=.75,
Path=self.filePath).getValue)
def cowlingPos(self):
"""
Cowling position of the engine, depends on the type of cowling
:Unit: [ ]
:rtype: float
"""
return float(
Importer(Component='Engine',
VariableName='Cowling position',
Default=.75,
Path=self.filePath).getValue)
def longPos(self):
"""
Gear position with regard to the MAC
:Unit: []
:rtype: float
"""
return float(Importer(Component='Landing Gear',
VariableName='Main Gear position',
Default=0.6,
Path=self.filePath).getValue)
def tailType(self):
"""
Tail type, could be "conventional", "cruciform" or "T tail"
:Unit: [ ]
:rtype: string
"""
return str(Importer(Component='Configuration',
VariableName='Tail Type',
Default='T tail',
Path=self.filePath).getValue)
def bypassRatio(self):
"""
Engine bypass-Ratio
:Unit: [ ]
:rtype: float
"""
return float(
Importer(Component='Engine',
VariableName='Engine bypass ratio',
Default=3.0,
Path=self.filePath).getValue)
def twRatio(self):
"""
Aircraft thrust to weight ratio
:Unit: [ ]
:rtype: float
"""
return float(
Importer(Component='Performance',
VariableName='Thrust to Weight ratio',
Default=.29145,
Path=self.filePath).getValue)
def enginePos(self):
"""
Engine position, could be either "wing" or "fuselage" mounted
:Unit: [ ]
:rtype: float
"""
return str(
Importer(Component='Configuration',
VariableName='engine Position',
Default='wing',
Path=self.filePath).getValue)
def nEngine(self):
"""
Number of engine of the aircraft
:Unit: [ ]
:rtype: integer
"""
return float(
Importer(Component='Configuration',
VariableName='nEngine',
Default=2.,
Path=self.filePath).getValue)
def engineStagger(self):
"""
Position of the engine with regard to the wing LE.
:Unit: [ ]
:rtype: float
"""
return float(
Importer(Component='Engine',
VariableName='Engine-LE stagger',
Default=-0.15,
Path=self.filePath).getValue)
def rho0(self):
"""
Air density at sea level - standard conditions
:Unit: [kg/m^3]
:rtype: float
"""
return float(
Importer(Component='Engine',
VariableName='Air density at sea level',
Default=1.225,
Path=self.filePath).getValue)
def TIT(self):
"""
Temperature at Inlet of Turbine
:Unit: [K]
:rtype: float
"""
return float(
Importer(Component='Engine',
VariableName='Temperature at Inlet of Turbine',
Default=1375.,
Path=self.filePath).getValue)
def noseLongPos(self):
"""
Gear position with regard to the fuselage length
:Unit: []
:rtype: float
"""
return float(Importer(Component='Landing Gear',
VariableName='Nose Gear position',
Default=0.08,
Path=self.filePath).getValue)
def etaNozzle(self):
"""
Efficiency of engine nozzle
:Unit: [ ]
:rtype: float
"""
return float(
Importer(Component='Engine',
VariableName='Nozzle efficiency',
Default=.97,
Path=self.filePath).getValue)
def a0(self):
"""
Speed of sound at sea level - standard conditions
:Unit: [m/s]
:rtype: float
"""
return float(
Importer(Component='Engine',
VariableName='Speed of sound at sea level',
Default=340.3,
Path=self.filePath).getValue)
def cowlingType(self):
"""
Cowling type of the engine, could be either "full" or "partial"
:Unit: [ ]
:rtype: string
"""
return str(
Importer(Component='Engine',
VariableName='Cowling type',
Default='partial',
Path=self.filePath).getValue)
