An Inverse Design Method for Wing Shape Optimization Guided by Spanwise Lift Distribution

In order to pursue the ultimate aerodynamic performance of aircraft, the development of aerodynamic shape optimization methods suitable for engineering applications has become increasingly important. From the engineering application point of view, it is necessary to study the flow structure of a wing in terms of spanwise lift distribution. The spanwise lift distribution not only affects the aerodynamic performance of the aircraft but also affects the structural design. Using the surrogate-based method, an efficient method for optimizing the aerodynamic shape of a wing guided by spanwise lift distribution is proposed. By introducing spanwise lift distribution parameters into the design objectives, this method enables the achievement of the desired lift distribution and meets design requirements. To verify its correctness, we perform the aerodynamic shape optimization of the Common Research Model (CRM) wing-only configuration. This paper investigates two optimization cases, where the lift coefficient is fixed at 0.5 and there are 84 design variables. Additionally, the maximum thickness of the CRM wing section is required to be equal to or greater than the baseline thickness. In the first case, direct drag reduction optimization is performed on the CRM wing. In the second case, using the lift distribution and minimizing drag coefficient as the design optimization objectives. The results show that with almost unchanged spanwise lift distribution, the shock wave drag of the wing is also reduced.