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NACA 65-009 axial compressor CORNER SEPARATION/ STALL

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Old   September 11, 2019, 00:03
Default NACA 65-009 axial compressor CORNER SEPARATION/ STALL
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Ankitha Chiluka
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My thesis is about NACA 65-009 Axial compressor cascade. Iíve already made the3D 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
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Old   September 17, 2019, 11:56
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Hello.


I am doing a simulation of axial turbine with focus on tip clearance flow. I am using SST turbulence model and it seems to be suitable:
http://fluid.itcmp.pwr.wroc.pl/~pbla...mation/sst.pdf


One of the many ways to display flow separation regions is to use surface streamlines. For any other use google images and see how do they show corner separation.
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Old   January 18, 2022, 11:50
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Sakun
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Hi,

i am trying to simulate NACA 65-009 as well but i could not find the full set of coordinates.
much appreciate if you can send me the coordinates or how to find them.
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angle of attack, axial compressor, corner separation, naca 65 series, stall

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