Stall Investigation Over a Wing, ANSYS Fluent CFD Simulation Training

$330.00 Student Discount

  • The problem numerically simulates the Stall phenomenon over a Wing using ANSYS Fluent software.
  • We design the 3-D model by the Design Modeler software.
  • We Mesh the model by ANSYS Meshing software.
  • The air is assumed to be incompressible.


Special Offers For Single Product

If you need the Geometry designing and Mesh generation training video for one product, you can choose this option.
If you need expert consultation through the training video, this option gives you 1-hour technical support.
The journal file in ANSYS Fluent is used to record and automate simulations for repeatability and batch processing.
editable geometry and mesh allows users to create and modify geometry and mesh to define the computational domain for simulations.
The case and data files in ANSYS Fluent store the simulation setup and results, respectively, for analysis and post-processing.
Geometry, Mesh, and CFD Simulation methodologygy explanation, result analysis and conclusion
The MR CFD certification can be a valuable addition to a student resume, and passing the interactive test can demonstrate a strong understanding of CFD simulation principles and techniques related to this product.



This project investigates the stall phenomenon over a wing using CFD simulation in ANSYS Fluent software. We perform this CFD project and investigate it by CFD analysis.

An airfoil is a streamlined shape capable of generating significantly more lift than its drag. Subsonic flight airfoils have a characteristic shape with a rounded leading edge, followed by a sharp trailing edge, often with a symmetric curvature of upper and lower surfaces.

The present model is designed in three dimensions using the Design Modeler software. This geometry is meshed in Ansys meshing software.

Stall Methodology

We employed a wing plane airfoil in this study and evaluated the stall angle using a CFD solver.

Also, the air is assumed to be incompressible and isothermal. The geometry is a 3-meter airfoil inside a 60-meter wind tunnel. Also, the maximum speed of 10 m/s is selected for the inlet.

Moreover, the SST k-omega model has been used to solve fluid equations due to its advantage in predicting flow patterns near and far from the surfaces.

Stall Conclusion

At the end of the solution process, we obtain two- and three-dimensional contours related to pressure, velocity, streamlines, and velocity vectors.

Furthermore, the maximum velocity value was found at the top surface of the airfoil, while the maximum pressure value was at the leading edge, where the velocity was minimum.

Additionally, the streamlines illustrate the quality of the flow streams resolved in the wake section, which is the core challenge of aerodynamic simulation and brings insight into the problem.

We rotated our current airfoil by the angle of 5 from zero to 45 degrees to identify the stall angle. By doing so, the drag and lift values were increased until the angle of 22.5 degrees, when the lift value started to decrease. The noted was found to be the stall angle and corresponded to the maximum lift value.



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