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Load factor as a result of constant roll rate

  1. Feb 3, 2015 #1
    The fuel pressure load equation for an aircraft in a constant roll maneuver has the term (as a result of the roll maneuver):

    [itex]\frac{\dot{\phi^2}}{2g}R^2[/itex]

    where

    [itex]R[/itex] - radius from center of fuselage
    [itex]g[/itex] - gravitational constant
    [itex]\dot{\phi}[/itex] - roll rate

    my question is where does the "2" next to the gravitational constant come from?
     
  2. jcsd
  3. Feb 9, 2015 #2
    Thanks for the post! This is an automated courtesy bump. Sorry you aren't generating responses at the moment. Do you have any further information, come to any new conclusions or is it possible to reword the post?
     
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