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Issue plotting Cp distribution graph for an airfoil

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Old   November 12, 2019, 14:09
Default Issue plotting Cp distribution graph for an airfoil
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lewis donnelly
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Evening all,

I followed a similar thread on here in order to plot a graph of the pressure coefficient against x/L (distance along airfoil surface) for a 2D airfoil. However regardless of whether I choose 'Pressure' or 'Pressure coefficient' under my y-axis scalar quantity, I get the absolute pressure along the airfoil surface.

Am I doing something wrong here as I don't understand why pressure and pressure coefficient would give me identical results?

For reference I have attached images of my results, my expected rough results and a screenshot of my command window within STAR CCM+ showing my selections.

Any help is much appreciated!

Lewis

correct pressure distribution.jpg

pressure distribution curve.jpg

command window for distribution curve.PNG
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Old   November 13, 2019, 12:56
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Lucky Tran
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go to the way bottom of the tree and go to Tools>Field Functions>Pressure Coefficient and check the reference properties.
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Old   November 13, 2019, 14:24
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Thanks for the reply!

Changing these values only seems to alter the scale of the y axis, however it still appears to be plotting the pressure as opposed to the coefficient of pressure! The graph shape is identical to absolute pressure, and I'm not too sure why this is.
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2d airfoil, distribution curve, pressure coefficient, star ccm+

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