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Center of pressure problem

  1. Feb 12, 2006 #1
    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
  2. jcsd
  3. Feb 12, 2006 #2


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    Staff: Mentor

    Center of pressure (cop). The point at which the aerodynamic lift on a rocket is centered. (from www.daviddarling.info/encyclopedia/C/center_of_pressure.html[/URL])

    Perhaps try this approach as applied to the foil.

    Last edited by a moderator: Apr 22, 2017
  4. Feb 12, 2006 #3
    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.
  5. Feb 13, 2006 #4


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    Can you give the exact wording of the problem?
  6. Feb 13, 2006 #5
    "Find the center of pressure for the upper surface of the airfoil (in terms of %chord from the leading edge)."

    I was trying to get the picture from the problem posted up here, but I haven't been able to so far.
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