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Aerospace Calculating reduction in static temperature and pressure

  1. Jun 11, 2009 #1
    When air is induced into a gas turbine inlet, the increase in velocity of the air will lead to an associated reduction in static temperatue and static pressure.
    How do you calculate these, that is, reduced static temp and pressures, given only Mach number, gamma, and perhaps total pressure ?

    The whole idea is to analyse whether condensation will take place or not. Kindly help.
  2. jcsd
  3. Jun 16, 2009 #2
    It depends on the pressure to which the air is expanded. Plot the things on a T-s diagram, & properties can be calculated
  4. Jun 17, 2009 #3
    Not sure what you mean by gamma, but last I checked can't isnt total pressure the sum of static and dynamic. Since you have the speed of the air you should be able to determine the dynamic pressure. Investigate bernoulis equation
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