1 import numpy as np 2 from math import sqrt 3 4 5 def _get_lift_rectangular(aircraft, lift=50): 6 L_prime = np.array([ 7 lift / (aircraft.wing.semi_span * 2) 8 for _ in range(aircraft.wing.semi_span) 9 ]) 10 return L_prime 11 12 13 def _get_lift_elliptical(aircraft, L_0=3.2): 14 L_prime = np.array([ 15 0.5 * L_0 / (aircraft.wing.semi_span * 2) * 16 sqrt(1 - (y / aircraft.wing.semi_span)**2) 17 for y in range(aircraft.wing.semi_span) 18 ]) 19 return L_prime 20 21 22 def get_lift_total(aircraft): 23 """Combination of rectangular and elliptical lift.""" 24 # F_z = self._get_lift_rectangular(aircraft) + self._get_lift_elliptical( 25 # aircraft) 26 # F_z = self._get_lift_rectangular( 27 # aircraft) + self._get_lift_elliptical(aircraft) / 2 28 # F_z = [i + j for i, j in self._get_lift_rectangular] 29 # return F_z 30 return 400 31