Shock Wave in a Supersonic Airflow, Transient Solver

$180.00 Student Discount

  • The problem numerically simulates Shock waves in a Supersonic Airflow using ANSYS Fluent software.
  • We design the 3-D model by the Design Modeler software.
  • We Mesh the model by ANSYS Meshing software, and the element number equals 4466857.
  • We perform this simulation as unsteady (Transient).
  • We use the Density-Based solver to define the compressible flow.


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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.


Shock Wave in a Supersonic Airflow with Transient Solver, ANSYS Fluent CFD Simulation Training

The problem is to simulate the supersonic airflow encountered by a two-way oblique airfoil barrier passing through a channel. So, we investigate fluid behavior and create a Shock Wave phenomenon by ANSYS Fluent software. We perform this CFD project and investigate it by CFD analysis.

The airflow in the simulation environment around the obstacles and canals has a temperature of 129.46 Kelvin and a Mach number of 2.49. The airflow direction is generally assumed to be in the same direction.

Mach number is a non-dimensional number that indicates the ratio of fluid velocity to sound velocity in the same fluid. This number is usually used when the velocity of the fluid flow is close to the sound velocity or more, and one of the major uses is aerospace applications.

We design the present 3-D model using the Design Modeler software. Then we mesh the present model using ANSYS Meshing software. The mesh type is unstructured, and the element number is 4466857.

Shik Wave Methodology

We use the Density-Based solver to define the compressible flow. In the shocking phenomenon, the airflow is considered quite compressible, and the Mach number is significantly high. It should be noted that the present problem is done in an unsteady state.

Shock Wave Conclusion

After the solution process is complete, we obtain two-dimensional and three-dimensional contours of pressure, temperature, velocity, density, and Mach number, as well as two-dimensional and three-dimensional pathlines.

We obtain the resulting contours and pathlines in the final second of the unsteady simulation process.

The results show that the shock is well formed. The shock occurred when the current collided with the sharp points of the geometry, and the Mach number changed abruptly. Pressure changes in the shock formation areas of the contours are evident.


  1. Torey Bernier

    Can this simulation be customized to model specific supersonic flow conditions?

    • MR CFD Support

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

  2. Mrs. Christa Sanford

    Can this simulation be used to optimize the design of supersonic aircraft?

    • MR CFD Support

      Absolutely! The results from this simulation can provide valuable insights into the shock wave behavior, which can be used for optimizing the design of supersonic aircraft.

  3. Dr. Gust Hill

    The training was excellent and of high quality. I was delighted.

  4. Rosario Walker

    I prepared for one of my university projects and realized what I had to do.

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