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.