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Aerospace Reynolds number for case flow over airfoil

  1. Mar 25, 2012 #1
    In which range of Reynolds numeber is laminar flow for airfoil?
    Is it Re < 5 x 10^5?
    How about turbulence case?
     
  2. jcsd
  3. Mar 25, 2012 #2

    boneh3ad

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    There is no general transition point Retnolds number. It depends on the shape of te airfoil and the surface roughness of the airfoil and the freestream flow quality and a host of other things besides Reynolds number. Typically though, even in a noisy wind tunnel the transition Retnolds number will be well into the millions. Still, that is very much an overgeneralization.
     
  4. Mar 25, 2012 #3
    The reynolds number for internal flow are much more easier.
    My airfoil is NACA 0012 symmetrical airofoil.
    Currently running on CFD simulation
     
  5. Mar 25, 2012 #4

    boneh3ad

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    Yes but internal flow is fundamentally different. Even on a simple flat plate there is no way to determine the transition Reynolds number in general.
     
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