Optimization of General Aviation Aircrafts Wing Design to Achieve the Optimal Range and Meet Performance Requirements Using Non-Dominated Sorting Genetic Algorithms II

The main idea of this paper is to find the optimal aircraft wing design for general aviation aircraft to reach the maximum range with the lowest possible weight and satisfying performance requirements at the same time. The use of the non-dominated sorting genetic algorithm II (NSGA-II) as an optimization tool for designing an aircraft can help to reduce the number of qualitative decisions. Also, the time and the cost of design can considerably be reduced. Objective functions for the optimization were minimization of wing weight and maximization aircraft range that as well as Restricting design parameters, six functional constraints are applied. The first functional constrain was fuel tank volume in the aircraft wing which must be able to incorporate the maximum fuel and the second functional constrain was lift coefficient which should be equal to the aircraft ideal cruise lift coefficient, since, in a cruising flight, the aircraft weight is equal to the lift force. the third functional constrain was stall speed which must be less than the target’s aircraft stall speed, the fourth and fifth were take-off ground run and landing ground run to zero speed on the runway which must be less than the target’s aircraft and the last one was the speed for the best rate of the climb which should be equal to ۱.۲ times more than stall speed. Design parameters were root chord, wingspan, and maximum thickness to chord ratio. Finally, validation was performed between the proposed values and target aircraft.