Eventos Anais de eventos
ENCIT 2022
19th Brazilian Congress of Thermal Sciences and Engineering
Solution of Transonic Flow Over a Supercritical Wing With Forced Oscillation
Submission Author:
Pedro Vinicius Souza Coimbra , SP , Brazil
Co-Authors:
Pedro Vinicius Souza Coimbra, Henrique Matos Campos, ALUISIO PANTALEAO
Presenter: Pedro Vinicius Souza Coimbra
doi://10.26678/ABCM.ENCIT2022.CIT22-0442
Abstract
Aeroelasticity is the subject that describes the interaction of aerodynamic, inertia, and elastic forces for a flexible structure and the phenomena that can result. Understanding aeroelasticity is vital in aircraft design, and due to that, the National Aeronautics and Space Administration (NASA) aims to bring innovation to this field with the Aeroelastic Perdition Workshop (AePW). This workshop is organized to assess the state-of-the-art computational methods for predicting unsteady flow fields and aeroelastic responses. The goals are to provide an impartial forum to evaluate the effectiveness of existing computer codes and modeling techniques and to identify computational and experimental areas needing additional research and development. In the second edition of AePW (AePW-2), experimental data for the Benchmark Supercritical Wing (BSCW) were provided, including wing configurations for static, forced oscillation, and flutter conditions. 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 AePW-2, doing the preprocessing and mesh generation in Salome Platform and the numerical solution in SU2. The selected test case consisted of the BSCW wing 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 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. In the final paper, we will detail the validation study and present the results obtained for the unsteady and forced oscillation case.
Keywords
CFD, Transonic Flows, Open Source Software, SU2, AePW-2
