Solution of transonic flow over a supercritical wing with forced oscillation

Abstract

The fundamental challenge in computational aeroelasticity is providing accurate data on the behavior of aerodynamic forces when coupled with flexible structures. This work aims to develop a numerical methodology to solve transonic flows over wings with forced oscillation using only open-source software. To accomplish our goal, we analyzed the test case 3B from the AePW-2 workshop, doing the preprocessing and mesh generation in Salome Platform and the numerical solution in SU2. The selected test case consisted of the Benchmark Supercritical Wing (BSCW) in a forced oscillation with a frequency of 10 Hz and 1° of amplitude. In the studied case, the Mach number was 0.85, and the angle of attack (AOA) was 5°. Since the analyzed flow is considered turbulent, we used the RANS equations and the SA turbulence model to model the turbulence. We validated our methodology by doing the Grid Convergence Index (GCI) analysis, considering a steady-state flow and the wing stationary being the convergence achieved between the fine and the medium mesh with a GCI of 2.2%. The results obtained presented good agreement with the experimental data.