def test_Class_Two(self): print('================ test Two ====================') acBd = BadaAircraftDatabase() assert acBd.read() atmosphere = Atmosphere() earth = Earth() aircraftICAOcode = 'A320' if ( acBd.aircraftExists(aircraftICAOcode) and acBd.aircraftPerformanceFileExists(aircraftICAOcode)): print(acBd.getAircraftFullName(aircraftICAOcode)) aircraftPerformance = AircraftPerformance(acBd.getAircraftPerformanceFile(aircraftICAOcode)) aeroDynamics = AeroDynamics(aircraftPerformance, atmosphere, earth) print(aeroDynamics) phase = 'XX' try: print(aeroDynamics.getDragCoeff(phase)) except Exception as e: print('test two = {0}'.format(e)) self.assertTrue(isinstance(e, AssertionError))
def test_Class_One(self): print('================ test one ====================') acBd = BadaAircraftDatabase() assert acBd.read() atmosphere = Atmosphere() earth = Earth() aircraftICAOcode = 'A320' if ( acBd.aircraftExists(aircraftICAOcode) and acBd.aircraftPerformanceFileExists(aircraftICAOcode)): print(acBd.getAircraftFullName(aircraftICAOcode)) aircraftPerformance = AircraftPerformance(acBd.getAircraftPerformanceFile(aircraftICAOcode)) aeroDynamics = AeroDynamics(aircraftPerformance, atmosphere, earth) print(aeroDynamics) for phase in ['CR', 'IC', 'TO', 'AP', 'LD']: print('phase= {0} - Vstall CAS= {1} knots'.format(phase, aeroDynamics.getVstallKcas(phase))) for phase in ['CR', 'IC', 'TO', 'AP', 'LD']: print('phase= {0} - Drag Coeff= {1}'.format(phase, aeroDynamics.getDragCoeff(phase))) print('Wing Area Surface={0} Square-meters'.format(aeroDynamics.getWingAreaSurfaceSquareMeters()))
def test_Class_One(self): print('================ test one ====================') acBd = BadaAircraftDatabase() assert acBd.read() aircraftICAOcode = 'A320' if (acBd.aircraftExists(aircraftICAOcode) and acBd.aircraftPerformanceFileExists(aircraftICAOcode)): print(acBd.getAircraftFullName(aircraftICAOcode)) aircraftPerformance = AircraftPerformance( acBd.getAircraftPerformanceFile(aircraftICAOcode)) aircraftMass = AircraftMass(aircraftPerformance)
def test_Class_Two(self): print('================ test Two ====================') acBd = BadaAircraftDatabase() assert acBd.read() aircraftICAOcode = 'A320' if ( acBd.aircraftExists(aircraftICAOcode) and acBd.aircraftPerformanceFileExists(aircraftICAOcode)): print(acBd.getAircraftFullName(aircraftICAOcode)) aircraftPerformance = AircraftPerformance(acBd.getAircraftPerformanceFile(aircraftICAOcode)) engine = Engine(aircraftPerformance) print('engine fuel consumption coeff= {0}'.format(engine.getFuelConsumptionCoeff()))
def test_Class_Four(self): print('================ test Four ====================') acBd = BadaAircraftDatabase() assert acBd.read() aircraftICAOcode = 'A320' if ( acBd.aircraftExists(aircraftICAOcode) and acBd.aircraftPerformanceFileExists(aircraftICAOcode)): print(acBd.getAircraftFullName(aircraftICAOcode)) aircraftPerformance = AircraftPerformance(acBd.getAircraftPerformanceFile(aircraftICAOcode)) engine = Engine(aircraftPerformance) for index in range(0,5): print(index) print('engine Descent Thrust Coeff= {0}'.format(engine.getDescentThrustCoeff(index)))
def test_Class_One(self): print('================ test one ====================') acBd = BadaAircraftDatabase() assert acBd.read() aircraftICAOcode = 'A320' if ( acBd.aircraftExists(aircraftICAOcode) and acBd.aircraftPerformanceFileExists(aircraftICAOcode)): print(acBd.getAircraftFullName(aircraftICAOcode)) aircraftPerformance = AircraftPerformance(acBd.getAircraftPerformanceFile(aircraftICAOcode)) engine = Engine(aircraftPerformance) print('engine is Jet= {0}'.format(engine.isJet())) print('engine is Turbo Prop= {0}'.format(engine.isTurboProp())) print( 'engine is Piston= {0}'.format(engine.isPiston())) self.assertTrue(engine.isJet(), 'A320 is a jet aircraft')
def test_Class_Three(self): print '================ test Three ====================' acBd = BadaAircraftDatabase() assert acBd.read() aircraftICAOcode = 'A320' if (acBd.aircraftExists(aircraftICAOcode) and acBd.aircraftPerformanceFileExists(aircraftICAOcode)): print acBd.getAircraftFullName(aircraftICAOcode) aircraftPerformance = AircraftPerformance( acBd.getAircraftPerformanceFile(aircraftICAOcode)) engine = Engine(aircraftPerformance) for index in range(0, 5): print index print 'engine Max Climb Thrust coeff= {0}'.format( engine.getMaxClimbThrustCoeff(index))
def test_Class_One(self): print('================ test one ====================') acBd = BadaAircraftDatabase() assert acBd.read() atmosphere = Atmosphere() earth = Earth() aircraftICAOcode = 'A320' if (acBd.aircraftExists(aircraftICAOcode) and acBd.aircraftPerformanceFileExists(aircraftICAOcode)): print(acBd.getAircraftFullName(aircraftICAOcode)) aircraftPerformance = AircraftPerformance( acBd.getAircraftPerformanceFile(aircraftICAOcode)) flightEnvelope = FlightEnvelope( aircraftPerformance=aircraftPerformance, ICAOcode=aircraftICAOcode, atmosphere=atmosphere, earth=earth) print(flightEnvelope)