A Sequential Approach for Aerodynamic Shape Optimization with Topology Optimization of Airfoils

The objective of this work is to study the coupling two efficient optimization techniques, Aerodynamic Shape Optimization (ASO) and Topology (TO), in 2D airfoils. To achieve such goal open-source codes, SU2 Calculix, are employed for ASO TO, respectively, using Sequential Least SQuares Programming (SLSQP) Bi-directional Evolutionary Structural (BESO) algorithms; latter well-known allowing addition material TO which constitutes, as far our knowledge, a novelty kind application. These codes linked by means script capable reading geometry pressure distribution obtained from defining boundary conditions be applied TO. Free-Form Deformation technique chosen definition design variables used ASO, while densities inner elements defined As test case, widely benchmark transonic airfoil, RAE2822, here with an internal geometric constraint simulate wing-box wing. First, procedures tested separately gain insight then run sequential way cases available experimental data: (i) Mach 0.729 at α=2.31°; (ii) 0.730 α=2.79°. In problem, lift fixed drag minimized; compliance minimization set prescribed volume fraction. Improvements both aerodynamic structural performance found, expected: reduced total on airfoil surface order minimize drag, resulted lower stress values experienced structure.