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Aerospace Static pressure in Compressor, Burner, Turbine

  1. Feb 18, 2011 #1
    I posted a question about this a couple days ago but I have since solved for the total temperatures in the compressor, burner, and turbine.

    My question is this. How do I calculate the static pressure in the compressor, burner, and turbine when i know the following data at each station?

    Known:
    Mach #
    Static Temperature
    Total Pressure
    Static Temperature
    speed of sound
    velocity
    mass flow rate

    I need to know the static temperature so I can calculate the density, which then leads to calculating the area.
     
  2. jcsd
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