Supersonic Nozzle Flow Separation and Shock Wave

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  • The problem numerically simulates the performance of phase change materials (PCM) in a storage tank using ANSYS Fluent software.
  • We design the 2-D model by the Design Modeler software.
  • We Mesh the model by ANSYS Meshing software,
  • We use a Density-Based solver to define the compressible flow.
  • The mesh type is Structured, and the element number equals 9000.
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Supersonic Nozzle Flow Separation (Shock Wave), ANSYS Fluent CFD Simulation Tutorial

The present study simulates Supersonic Nozzle Flow Separation within a supersonic convergent-divergent nozzle. It examines the behavior of airflow separation from the nozzle in the surrounding environment by ANSYS Fluent software. We perform this CFD project and investigate it by CFD analysis.

The functional structure of the nozzle is such that as the fluid enters it and passes through the convergent part of the nozzle, according to the continuity equation, it causes the velocity of the passing fluid to increase by decreasing the cross-sectional area of the flow. Therefore, due to Bernoulli’s law, the fluid pressure decreases with increasing velocity.

Parameters such as Mach number, velocity, and pressure based on the fluid flow’s motion in the nozzle’s longitudinal direction have been investigated to analyze this model.

The following figure shows a schematic of the internal structure of a convergent-divergent nozzle and its components.

The present 2-D model is drawn using Design Modeler software. The geometric structure of the model consists of a convergent-divergent nozzle and the throat area, as well as a rectangular space containing the nozzle output.

The meshing of the present model has been done using ANSYS Meshing software. The mesh type is structured and the element number is 9000.

Supersonic Methodology

We have enabled a density-based solver due to the compressibility of this project. The nozzle pressure ratio (NPR) is equivalent to the ratio of the inlet air pressure of the nozzle to the ambient pressure.

Thus, the value of the nozzle pressure ratio in the current system is 1.5, and the amount of inlet air pressure is 153580.65 Pascals (NPR = P / P_ambient = 1.5 and therefore P = 1.5 * 102387.146), as well as the pressure at the output, is equal to the ambient pressure, that is 102387.146 Pascal.

In addition, the inlet airflow has a temperature of 290 Kelvin.

Supersonic Conclusion

At the end of the solution process, we obtain two-dimensional contours of pressure, temperature, velocity, density, Mach number, and two-dimensional path lines.

As seen from the contours, Mach has increased in the nozzle opening. Therefore, it can be said that this type of nozzle, by changing the cross-section, causes the Mach number to enter along the range.

Increasing the Mach number in the nozzle opening reduces the pressure and reciprocally the temperature in the nozzle opening and therefore during the nozzle.

1 review for Supersonic Nozzle Flow Separation and Shock Wave

  1. Avatar Of Pierce Reichel Md

    Pierce Reichel MD

    The use of CFD in this simulation is truly innovative!

  2. Avatar Of Prof. Hayley Torphy Dds

    Prof. Hayley Torphy DDS

    Can I contribute to this simulation?

    • Avatar Of Mr Cfd Support

      MR CFD Support

      We are open to contributions! Please share your ideas or suggestions.

  3. Avatar Of Donny Hane

    Donny Hane

    How are the results of the simulation visualized?

    • Avatar Of Mr Cfd Support

      MR CFD Support

      The results are visualized using contour plots of temperature, pressure, velocity, and Mach number, as well as pathlines of the flow.

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