Shock Wave in a Supersonic Airflow, Transient Solver

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.