def compute_flight_points(self, flight_point: FlightPoint):
if flight_point.thrust_is_regulated or flight_point.thrust_rate is None:
flight_point.thrust_rate = flight_point.thrust / self.max_thrust
else:
flight_point.thrust = self.max_thrust * flight_point.thrust_rate
flight_point.sfc = self.max_sfc * (1.0 + flight_point.thrust_rate) / 2.0
def _compute_propulsion(self, flight_point: FlightPoint):
flight_point.thrust_rate = self.thrust_rate
flight_point.thrust_is_regulated = False
self.propulsion.compute_flight_points(flight_point)
