Imam Hussein University Fluid Mechanics & Aerodynamics 2322-3278 10 2 2022 02 20 Aerolastic Around Rough Airfoil During Turbulent Unsteady Transonic Flow Aerolastic Around Rough Airfoil During Turbulent Unsteady Transonic Flow 19 34 206908 FA M.R. Saber PhD student Ferdowsi University of Mashhad, Mashhad, Iran Mohammad Hassan Djavareshkian Professor, Ferdowsi University of Mashhad, Mashhad, Iran Journal Article 2021 05 30 In this paper, the effect of roughness and stiffness on the aeroelasticity of an oscillating airfoil during turbulent unsteady transonic flow has been studied. In this simulation, the finite volume method is used to discretize the equations to solve the Navier-Stokes equations. In this pressure-based algorithm, a high-resolution scheme for convection term and 𝜿-ε turbulence model are used. For computing convection terms, a Normalized Variable Diagram technique is used. Here the technique of inlet velocity vector oscillation is applied. In addition, a modified 𝜿-ε model for compressible flow is applied to simulate Navier Stokes equations. The two-dimensional motion equations are obtained from the Lagrangian equations, which are combined with the aerodynamic equations. The results of validation show that the extracted data has a desirable accuracy. Furthermore, the FSI results show that, for rough airfoils, the strength of the shock wave is weakened, the shock wave moves to the trailing edge, and the oscillation of the airfoil is reduced. Also, with increasing structural stiffness, the damping of oscillations increases, and drag decreases. In this paper, the effect of roughness and stiffness on the aeroelasticity of an oscillating airfoil during turbulent unsteady transonic flow has been studied. In this simulation, the finite volume method is used to discretize the equations to solve the Navier-Stokes equations. In this pressure-based algorithm, a high-resolution scheme for convection term and 𝜿-ε turbulence model are used. For computing convection terms, a Normalized Variable Diagram technique is used. Here the technique of inlet velocity vector oscillation is applied. In addition, a modified 𝜿-ε model for compressible flow is applied to simulate Navier Stokes equations. The two-dimensional motion equations are obtained from the Lagrangian equations, which are combined with the aerodynamic equations. The results of validation show that the extracted data has a desirable accuracy. Furthermore, the FSI results show that, for rough airfoils, the strength of the shock wave is weakened, the shock wave moves to the trailing edge, and the oscillation of the airfoil is reduced. Also, with increasing structural stiffness, the damping of oscillations increases, and drag decreases.

https://fma.ihu.ac.ir/article_206908_324608297d9433d611744bcfb1974bd6.pdf