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)