Comparison between computational and experimental non-stationary pressure distribution on a pitch-oscilating wing

The objective of this work is to obtain CFD results for the dynamic response of a wing oscillating in pitch in a transonic regime using an open-source tool. The purpose is to verify and improve the correspondence with the experimental data as performed in the wind tunnel test for a wing model developed by Embraer. For this, in some analyzes it is proposed to impose a prescribed movement to the wing in the CFD simulations that models the bending observed in the scaled model throughout the tests as a rigid mesh movement in rolling direction. Prescribed motion parameters are extracted directly from the model’s structural deformation measurement data. In addition, simulations of a test case using the Benchmark Supercritical Wing (BSCW) are performed to investigate the impact of relevant variables in this type of analysis, such as time step and mesh refinement level. The time step was identified as the most influential parameter to approximate the simulation results to experimentally obtained data. The CFD results for the Embraer wing were able to capture the main behaviors of the magnitude and phase of the non-stationary pressure coefficient on the wing, mainly for conditions of higher reduced frequencies, with an affordable computational cost.