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Axial compressor Blade NACA 65-009 , To identify stall/ corner separation

    • ankithachiluka
      Subscriber

      Hi everybody,


      I was attempting to show corner separation contours on NACA65-009 compressor blade by varying angle of attack and surface roughness.


      My thesis is about NACA 65-009 Axial compressor cascade. I’ve already done the model in design modeler, ANSYS.


      How do i show corner separation (leading to corner stall at the Hub) by varying angle of attacks and surface roughness. Could you tell me this in detail, how to go about this? Which parameters should i consider to show it, which turbulence model? I wanted to do it on ANSYS CFX.


      What inputs should i be giving to show pressure, velocity and streamlines contours showing corner separation ( at the junction of the suction surface and trailing edge). I had previously used 99 kpa as input and 121kpa as output.


      Thanks in advance 

    • Rob
      Ansys Employee

      There are a couple of airfoil and some compessor/turbine YouTube videos, I'd start with those and then review the tutorials supplied with the 2019 documentation. 

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