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Aerospace Confused with static pressure and total pressure and Bernoulli's eq!

  1. Sep 1, 2008 #1
    hi all, am a confused-being after trying to solve this really simple question..
    somewhere somehow my concepts are just not right ):

    Consider an airplane flying with a velocity of 60m/s at a standard altitude of 3km. At a point on the wing, the airflow velocity is 70m/s. Calculate the pressure at this point.

    By using p1+1/2(rou)(v1)^2=p2+1/2(rou)(v2)^2 and the standard atmospheric pressure table, the given solution is
    7.0121 X 10^4 + 1/2(9.0926X10^(-1))(60^2)/2 = P2 + 9.0926X10^(-1)(70^2)/2
    I do not understand why P1 = 7.0121 x 10^4 N (given in the table), where P1 should be the pressure at the point of the flow where velocity is 60m/s.
    What is the pressure given in the table referred to as?
    I am confused with static/dynamic and total pressure!

    Would any kind soul please help?
    Thanks alot in advance!
     
  2. jcsd
  3. Sep 1, 2008 #2
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