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Airfoil pressure

  1. Jul 22, 2007 #1

    velocity of air=0, an airfoil or wing with is moving forwards with a velocity of 40m/s at an altitude of 1100m. At a certain point close to the wing (which is a point on top of the wing) ,the air speed relative to the wing is 50m/s.Find the pressure at that point.

    Somebody pls help me.....

    I trz to use the formula of 1/2*(density)*(velocity)^2 + pressure + (density)*g*z which is bernoulli"s equation and is wrong.....

  2. jcsd
  3. Jul 23, 2007 #2
    1/2d*40*40 +p1=1/2d*50*50 +p2. I think this should be it. Is this what you did?
  4. Jul 23, 2007 #3
    yes,but how to get p1 and p2 ??
  5. Jul 23, 2007 #4


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  6. Jul 23, 2007 #5
    static air pressure equals to 1.23 * 9.81 * 1100m . Am I rite?? but the answer is wrong if I use this value...
  7. Jul 23, 2007 #6


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    Please provide the units!

    It would appear that one is using [itex] \rho{gh}[/itex], and therefore one is finding the pressure at the bottom of a column of air of 1100 m height. Of course, one can subtract that value from 1 atm and obtain an reasonable approximation of the air pressure at 1100m above sea level.
    Last edited: Jul 23, 2007
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