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Aerospace Velocity from Static and Total pressures

  1. Jan 4, 2010 #1
    Hi,
    I am becoming a bit stuck with a fairly cynical question.

    I want to work out the velocity of the fluid from the static and total pressures obtained in a wind tunnel experiment.
    The manometor was open to air (atmospheric) at one end and measuring static or total pressure at the other. Both readings were taken.

    To calculate the velocity p0=p+0.5*rho*u2

    Which all seems fine.
    Rearrange to find u

    However, the values I have are not Ptotal or Pstatic correct?
    I need to add atmospheric pressure to these?
    I have an equation which is:
    P0=patm-rho*g*h

    So for an example,
    patm=101081.39 Pa
    h? (Reading from manometor)=0.002
    So:
    101081.39-(1.2*9.81*0.002)=P0
    Would this indeed be the total pressure?

    Paul
     
  2. jcsd
  3. Jan 4, 2010 #2
    The manometer gives you the static pressure, which will be equal to the total pressure if it's placed at a stagnation point.
     
  4. Jan 4, 2010 #3
    Sorry, might not have been making it quite clear.
    The static pressure measurement was staking perpendicular to the flow and the total (stagnation) press was taken normal to the flow.
     
  5. Jan 4, 2010 #4
    Just use the bernoulli equation to back out the velocity, as per your textbook.
     
  6. Jan 4, 2010 #5
    Yes but I'm getting confused as to use as what in the bernoulli equation.
    The equation is stated in my original post to find the velocity...
     
  7. Jan 4, 2010 #6
    I believe your analysis is correct, but its been a few years since I've done that calculation so someone should double check my statement. I've become spoiled in getting data files of pressure measurements from digital instruments that I'm now rusty.
     
  8. Jan 4, 2010 #7

    FredGarvin

    User Avatar
    Science Advisor

    If both of your pressure readings are referenced to atm, then you simply use the delta between the dynamic and static pressure in your calculation.

    [tex]V =\sqrt{\frac{2 \Delta P}{\rho}}[/tex]

    That is assuming compressibility affects are negligible. If so you need to take that into account and is a function of Mach number.
     
  9. Jan 6, 2010 #8
    That's 14.66 psi, off just 0.0000034 psi from atmospheric, so that's not the total pressure.

    Fred's correct: use the differential pressure. Given your example, if it's representative, you'll not be encountering compressibility effects.
     
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