## Center of pressure problem

I have some intro aeronautical class homework problem that is giving me difficulty.

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
 PhysOrg.com science news on PhysOrg.com >> Ants and carnivorous plants conspire for mutualistic feeding>> Forecast for Titan: Wild weather could be ahead>> Researchers stitch defects into the world's thinnest semiconductor
 Admin Center of pressure (cop). The point at which the aerodynamic lift on a rocket is centered. (from http://www.daviddarling.info/encyclo..._pressure.html) Perhaps try this approach as applied to the foil. http://www.grc.nasa.gov/WWW/K-12/airplane/rktcp.html
 I've looked at methods similiar to what was on that page, however I don't think I have enough information from that problem to use this method. Do I have to know the velocity of the incoming flow in order to determine the center of pressure? I have a sort of triangle made for determining the center of the triangle. However, I only know the length of one side-the base is 1m. I know the pressure acting on another side, but that's all.

Recognitions:
Gold Member