FSI Analysis of NACA 0014 Airfoil: Aerodynamic Forces and Structural Response

Description

Introduction:

In this project, a NACA 0014 baseline is simulated to calculate net aerodynamic forces using a Fluid Solid Interaction (FSI) model. It is one way FSI simulation. So we can use the Structure Module provided in the new version of ANSYS Fluent Standalone.

Geometry and Mesh:

The geometry of this project was created using Design Modeler software. The size of the Geometry is 20*20*1 meters, with the airfoil located at its center. The geometry was inserted into the ANSYS Meshing software, and the software generated 1708222 unstructured mesh. Then, it was meshed in ANSYS Meshing, resulting in a smooth distribution of elements, along with a boundary layer to enhance accuracy.

FSI Methodology:

Governing equations solved at ANSYS Fluent software. A pressure-based solver and steady approach were employed. Additionally, the Spalart-Allmaras turbulency model was used for the viscous model, and the Linear Elasticity model was applied for structural analysis. The one-way FSI approach transfers the aerodynamic pressure loads from the fluid solution to the structural model without feeding back the resulting deformations to influence the flow field. This approach is appropriate for cases where structural deformations are expected to have minimal impact on the flow behavior. Additionally, a coupled algorithm was used to couple pressure and velocity.

Results:

The results are extracted, including the total displacement caused by aerodynamic forces, the stress applied based on the Von Mises relation, and the velocity and pressure distribution around the airfoil. Additionally, the software reports CL and CD coefficients as 0.446 and 0.010, respectively.