ANSYS Tutorial | Flow in a Convergent- Divergent Nozzle | Compressible Flow Part 1/2
Consider a convergent-divergent Nozzle in which Ideal Gas is flowing. At the inlet, the Stagnation Pressure is atmospheric pressure, at the exit the pressure is lower than the inlet. At the throat section of the nozzle, the velocity increases and pressure decreases. At the converging section, the flow was subsonic, and as the fluid accelerates towards the throat, the Mach no. increases and the flow become supersonic at the exit.
What to learn from this tutorial?
- Creating the axisymmetric nozzle geometry.
- Use of Face Split.
- Creating structured Mesh.
- Extracting Solution data for the desired result (Mach no).
- Density-based solver setup.
- Compressible fluid flow modeling.
- CFD Post Processing
Part 2 of the Tutorial: • ANSYS Tutorial | Flow in a Convergent...
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