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)