Transonic Flow over the 3D Airfoil (Naca 0012) CFD Simulation, ANSYS Fluent Tutorial
$150.00 Student Discount
- The present CFD Project simulates compressible air flow over Naca 0012 airfoil via ANSYS Fluent software.
- We modeled the geometry using ANSYS Design Modeler software and created the mesh using ANSYS Meshing software.
- The mesh type is structured, and the number of cells f is 1,560,000.
- The air property is selected as the ideal gas to model compressibility.
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In this project, the compressible air flow over Naca 0012 airfoil in 3-dimensional space is simulated. The 300K air enters the computational domain when the Mach number is assumed to be 0.7. The angle of attack is 2 degrees. This simulation focuses on using a pressure-based solver and a Coupled pressure-velocity coupling algorithm to model compressible flows instead of a Density-based approach.
First, the 2D geometry with several zone divisions was sketched and then extruded along the z-axis coordinate. Note that it was all done in Ansys Design Modeler software. In addition, the structured mesh grid was carried out in ANSYS Meshing software. As a result, 1,560,000 cells were generated.
Methodology: Transonic Flow over the 3D Airfoil
This simulation focuses on using a pressure-based solver and a Coupled pressure-velocity coupling algorithm along with the ideal-gas behavior of air density to model Compressible flows instead of a having Density-based approach. Also, the simulation is independent of Time, so it has performed in steady state form.
In this project, the Mach number of the flow was assumed to be 0.7, and there was transonic flow over the airfoil. Due to fluid compressibility, a density-based solver type should be hired. Still, we came up with using a pressure-based solver type and coupled velocity-pressure coupling algorithm. Also ideal-gas behavior of the density simultaneously. Notice that the viscosity was a function of temperature, so we used the Sutherland model.
As contours show, The velocity magnitude has a severe increase, and thereby, there is a pressure drop on the upper wall of the airfoil because of the 2-degree angle of attack. The pressure gradient generates lift and drag forces. Furthermore, there is a direct correlation between velocity and Mach number and similarly between density and pressure