I have some intro aeronautical class homework problem that is giving me difficulty.(adsbygoogle = window.adsbygoogle || []).push({});

I need to find the center of pressure for the upper surface of an airfoil in terms of percent chord from the leading edge. I know that the chord lenth is 1m. The pressure from the top surface of the airfoil starting at the chord is 3N/m. The pressure from the bottom surface of the airfoil starting at the chord is 1N/m. There is no angle of attack and I do not know the velocity of the incoming air.

Do I need to use the equation Cp=Pt-P/1/2pv^2 ?

I can't understand how to use this equation in the context of this problem.

Any help pointing me in the right direction would be appreciated

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# Center of pressure problem

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