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Lift and drag coefficient calculation

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Old   March 4, 2018, 12:23
Default Lift and drag coefficient calculation
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Andre
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Dear all,
I am attempting a CFD simulation with no formal training, only basic fluid dynamics. I am attempting to validate the use of a 2D CFD method so I can use it in my project. The aerofoil I am simulating is called NACA 24112; I am simulating it at 3.5 deg angle of attack and at 1mm chord scale. Due to the scale of my model in order to have a Reynolds number of 50,000 I would need to simulate at 700m/s which is beyond the method I am using.

http://airfoiltools.com/airfoil/deta...4112-jf#polars

My values of lift and drag co-efficient are HIGHLY dependent on the velocity of the flow which means I cannot match my data to the given data. The velocity profile seems reasonable. Can anyone help me validate this?
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Old   March 5, 2018, 12:04
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M Sereez
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How about trying to modify the dynamic viscosity at the inlet instead of modifying velocity? 700m/s is hypersonic speed.
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