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)
