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Aerospace Calculating Boundary Layer Thickness

  1. Aug 5, 2009 #1
    I am trying to calculate the thickness of the boundary layer for a NACA 2412 airfoil. I am working on constructing some wind tunnel tests that simulate a Cessna 172 (NACA 2412 airfoil). I am trying to determine the thickness of the boundary layer (distance from surface to 99% of free-stream velocity). What would the boundary layer thickness be (or what is the equation) for a NACA 2412 airfoil (chord length is about 1.3 m) with a velocity of 65 m/s at 3000m MSL (kinematic viscosity is about 1.8e-5).

    Preferably, I am looking for an equation that would be able to calculate this.

    Thank you.
     
  2. jcsd
  3. Aug 5, 2009 #2
    How did you jump from wind tunnel tests on a particular airfoil to that of a Cessna 172?
     
  4. Aug 5, 2009 #3
    The Cessna 172 information is irrelevant. I am using the NACA 2412 airfoil model for my experiments. I just need to determine boundary layer thickness for that.
     
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