Amirkabir University of Technology Amirkabir Journal of Mechanical Engineering 2008-6032 51 6 2020 02 20 Numerical Investigation of Flow Behavior Around Chordwise Morphing NACA 0012 Numerical Investigation of Flow Behavior Around Chordwise Morphing NACA 0012 1411 1426 2815 10.22060/mej.2018.13708.5699 FA Seyed Esmail Razavi Professor at University of Tabriz Mir Hossein Negahban M.Sc. Graduate Student of University of Tabriz Journal Article 2017 11 17 In the present study, numerical simulation of transonic flow around chordwise morphing airfoil has been accessed. Fluid-Structure interaction for analyzing flow field behavior in conjunction with morphing airfoil is used. In this regard, a two-dimensional finite element model is established and the arbitrary Lagrangian-Eulerian formulation (ALE), in the flow field and structure configuration is applied to accommodate the deforming boundaries and due to the good conformation of flow filed and deforming boundaries in this formulation, the distortion of computational grid is diminished after the deformation. The procedure incorporates the one-equation Spalart-Allmaras turbulence model which is a suitable model for aerodynamics. In this study, the preferable Mach number for the transonic regime is 0.7. Chordwise elastic deformability by uniformly varying extended parabolic load on both leading and trailing edges is considered for morphing purposes. The model is validated against conventional rigid airfoil for various angles of attack, and the comparisons show considerable improvement in the aerodynamic performance and prove the efficiency of elastic morphing airfoil. Moreover, the ultimate results indicate that chordwise morphing contributes to the best flight conditions for cruise flight which contains a wide flight endurance. All the simulations are steady-state and are carried out by COMSOL Multiphysics software. In the present study, numerical simulation of transonic flow around chordwise morphing airfoil has been accessed. Fluid-Structure interaction for analyzing flow field behavior in conjunction with morphing airfoil is used. In this regard, a two-dimensional finite element model is established and the arbitrary Lagrangian-Eulerian formulation (ALE), in the flow field and structure configuration is applied to accommodate the deforming boundaries and due to the good conformation of flow filed and deforming boundaries in this formulation, the distortion of computational grid is diminished after the deformation. The procedure incorporates the one-equation Spalart-Allmaras turbulence model which is a suitable model for aerodynamics. In this study, the preferable Mach number for the transonic regime is 0.7. Chordwise elastic deformability by uniformly varying extended parabolic load on both leading and trailing edges is considered for morphing purposes. The model is validated against conventional rigid airfoil for various angles of attack, and the comparisons show considerable improvement in the aerodynamic performance and prove the efficiency of elastic morphing airfoil. Moreover, the ultimate results indicate that chordwise morphing contributes to the best flight conditions for cruise flight which contains a wide flight endurance. All the simulations are steady-state and are carried out by COMSOL Multiphysics software. https://mej.aut.ac.ir/article_2815_f5b1b89d98b7286673128a5fb112cb9a.pdf