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2D axisymmetric Supersonic flow simulation

    • Zijing.zheng
      Subscriber

      Hi all,

      I try to analyze the front shock of a heat shield (red graph), and it seems to be messed up somewhere since the shock never comes out clear but lots of small waves within the shocks. I tried to make a bigger flow field or small size of the mesh but it did not seem to be working.

      So I took a step back and just do an angled hill and test from there (blue graph) but it also seems to be not working because that happens again even after 30,000 iterations or become invalid due to high residuals.

      My goal is to try to analyze the front shock of a heat shield which is shown in the Mach graph, ignoring the backflow. But I can't get a clean shock, and I keep getting waves within the shocks. So I took a step back to use an angled hill to test out the flow. But it still won't converge, and appear some reflect waves within the shock in the blue graph.

      For some reason, my flow keeps messing up even creating multiple different meshes. The following pictures are my setups and simulation results. I hope you guys can help me out.

      Solver: Density-based (I tried Pressure based, but it also didn't work)
      Turbulence model: Laminar ( I also tried spalart allamars)
      Velocity inlet from left to right as the pressure outlet
      the bottom is the axis, and the top is used as the wall but it is pretty far from the shock.

      the wall is in the right corner where a hill-shaped bump. (so the bottom be like three lines, axis - wall - wall )

      Velocity speed (960 m/s )
      initial pressure (52 pa for high altitude )
      material: air
      density: ideal gas
      viscosity: Sutherland law
      energy: on (automatic for ideal gas)

    • Amine Ben Hadj Ali
      Ansys Employee

      This might be of great value for you: "Shock-Expansion Theory | Ansys Innovation Courses"

      I will probably first adress the isssue of having the outlet near the concave corner / step.

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