|Aug5-09, 01:55 PM||#1|
Calculating Boundary Layer Thickness
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.
|Aug5-09, 06:47 PM||#2|
How did you jump from wind tunnel tests on a particular airfoil to that of a Cessna 172?
|Aug5-09, 08:36 PM||#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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