def analyze_body(self,body,name):
"""
analyzing revolution body object (fuselages with non-revolution body
shape are also analyzed)
Parameters
----------
body : aircraft.fuselage
fuselage or nacelle object
name : string
name of analyzed body. Can be arbitrary and will be used for
report generation
Returns
-------
bodyDrag : DragItem
drag of the fuselage with reference area specified while initialization
"""
self.set_reference_area()
bodyDrag = DragItem()
bodyDrag.name = name
self.add_body(body)
bodyDrag.CD = self.analyze()
bodyDrag.quantity = 1
bodyDrag.CDtotal = bodyDrag.CD
return bodyDrag
def analyze_wing(self,wing,name):
"""
analyzing friction and form drag of the wing-type bodies. Creates Component
object returns with all fields filled including geometry required for
drag analysis and drag value itself.
Parameters
----------
wing : aircraft.wing
wing, horizontal or vertical stabilizer object
name : string
name of the wing. Can be arbitrary and will be used for
report generation
"""
self.set_reference_area()
wingDrag = DragItem()
wingDrag.name = name
self.add_wing(wing)
wingDrag.CD = self.analyze()
wingDrag.quantity = 1
wingDrag.CDtotal = wingDrag.CD
return wingDrag