def __init__(self,aircraftInputSheet):
self._inputSheet =aircraftInputSheet
self.entryName =str(self._inputSheet.name)
self.name =self.entryName#str(self._inputSheet.cell(0,1).value)
self._readData()
self._get_volume_ratios()
# components mass and drag are calculated here
self.mass = weight.get_general_aviation_mass(self)
self.drag = drag.get_total_drag(self,self.designGoals.designSpeed,
self.designGoals.designAltitude,True)
# TODO: separate analysis into different methods
self.analysis =AircraftAnalysis.analysis(self)
def update_drag(self,velocity=0.0,altitude=0.0):
"""
Updates parasite drag of current configuration
Parameters
----------
velocity : float, m/sec
altitude : float, m
"""
if velocity<=0.0:
velocity=self.designGoals.designSpeed
if altitude<=0.0:
altitude=self.designGoals.designAltitude
self.drag = drag.get_total_drag(self,velocity,altitude)
