NACA 0012 Airfoil, Compressible Flow) CFD Simulation

$150.00 Student Discount

  • The problem numerically simulates NACA 0012 Airfoil (Compressible Flow) using ANSYS Fluent software.
  • We design the 2-D model by the Design Modeler software.
  • We Mesh the model by ANSYS Meshing.
  • The model mesh is structured, and 35000 cells have been created.
  • We apply a Density-based solver to define the compressible flow.
  • We determine the Mach number for the inlet boundary condition.

Click on Add To Cart and obtain the Geometry file, Mesh file, and a Comprehensive ANSYS Fluent Training Video. By the way, You can pay in installments through Klarna, Afterpay (Clearpay), and Affirm.

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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.

Description

Training Demo

NACA 0012 Airfoil (Compressible Flow) CFD Simulation, ANSYS Fluent Tutorial

This simulation is about NACA 0012 airfoil via ANSYS Fluent software. We perform this CFD project and investigate it by CFD analysis.

In general, the airfoil is the same as the plane’s wing cross-section, wind turbine blade, helicopter, and so on. However, it should be noted that different airfoils can be used to construct an aircraft wing, and the choice of airfoil type in different applications depends on the aerodynamic characteristics.

Geometric defining parameters include chord line, angle of attack, leading edge, and trailing edge. The direction of the airflow into the airfoil is defined by the angle of attack (the angle between the chord and the horizontal direction of the airflow velocity).

In the present case, the attack angle is 5 degrees; thus, the horizontal component of the airflow direction is defined as 0.996 (cos5), and the vertical component is equal to 0.087 (sin5).

This project aims to investigate the airflow behavior and the pressure distribution around the airfoil and study the drag and lift forces.

We design the geometry of the present model by Design Modeler software. We mesh the model with ANSYS Meshing software. The model mesh is structured, and 35000 cells have been created.

Airfoil Methodology

In this simulation, the density-based solver is performed because the airflow is considered compressible.

Defining the Mach number in the boundary conditions is necessary for compressible flows. The Mach number is equal to the ratio of the speed of an object in a fluid to the sound speed in the same fluid in which that object moves.

For example, the sound speed in the air with a temperature of 25 degrees Celsius is 343 meters per second.

In general, the simulation of an airfoil requires the definition of a far-field boundary condition, and therefore the Mach number for the flow field must be defined, the value of which in the present case is 0.6.

Airfoil Conclusion

After simulation, we obtain two-dimensional contours of pressure, velocity, temperature, density, and Mach number, as well as two-dimensional streamlines.

The results show that at the leading edge of the airfoil, the highest pressure appears, caused by the airflow’s direct contact with the airfoil’s leading edge.

The structure of the airfoil is such that the airflow on its upper surface faces the greatest pressure drop. This pressure difference between the top and bottom of the airfoil body causes the upward movement of the wing.

Also, the velocity changes are in perfect accordance with the pressure distribution. Where there is the greatest pressure, the least velocity appears, and vice versa.

Reviews

  1. Rasheed Larson

    Can this simulation be customized to model the airflow around different types of airfoils?

    • MR CFD Support

      Yes, we can accommodate your desired simulations. Please share more details about your specific requirements.

  2. Ms. Litzy Osinski

    Well done!

  3. Demond Mertz

    How accurate is this simulation?

    • MR CFD Support

      The simulation is based on well-established physical principles and mathematical models, and we validate our results against experimental data to ensure accuracy.

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