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Old   April 14, 2014, 09:36
Default CFX-Post: How to calculate pressure loss for Airfoil?
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Hello everyone,

I am having troubles to calculate the pressure loss for my simulation as I get negative results. I am using mesh similar to this one and want to calculate the pressure loss for different angles of attack.

So when I try to apply this formula

(p.total.1-p.total.2)/p.dynamic.1

by this:

=(areaAve(Total Pressure)@inlet -areaAve(Total Pressure)@outlet )/(0.5*areaAve(Density)@inlet*areaAve(Velocity)@inle t^2)

than for some cases I get this:

areaAve(Total Pressure)@inlet < areaAve(Total Pressure)@outlet

and therefore negative pressure loss values.

For Clarification:
inlet = circular arc
outlet = vertical line
I use diffrent velocity_u and velocity_v components to realizre the different angles.

Any Idea, what I am doing wrong?
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Old   April 14, 2014, 15:02
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Edmund Singer P.E.
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I suspect it has to do with the curved nature of your inlet and how you are defining your velocity.

Also, switch to massFlowAve(Total Pressure)
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