Boundary Layer thickness
Hi,
I have a CFD model and i am trying to improve the density of the mesh inside the BL via additional prism layers. One thing i want to know is how thick (aproximately) the BL is so i can calculate how many layers i need. Does anyone know a way of estimating the thickness of the BL? Cheers 
Most introductory heat transfer texts have chapters on how boundary layer models are developed starting with the NavierStokes equations. These eventually lead to algebraic expressions for b. l. thickness as a function of Reynolds Number or other appropriate dimensionless groupings of fluid properties, physical dimensions, and driving functions.
On my shelf of (antique) heat transfer texts are Schlichting (Boundary Layer Theory) and Chapman, (Heat Transfer). Others will be able to point to modern (and thus easier to find) texts. Good luck! 
BL Thickness
Hi,
If you're using commercial software try the user manual  CFX's details calculations for Y+ and B.L. thickness under "turbulence and near wall modelling". Good luck. Ianto 
Hi,
The way on which I usually calculate the boundary layer is: δ=5.2x/√Re 
3 dimensional wing with winglet design Using Catia
hello, I am in problem in Design wing with winglet using catia. I have design 3 dimensional wing with taper, sweep ang twist. But i cant design winglet on the tip. I will analize the design with Fluent. Anyone could help me....:confused:

empirical formula for B.L. thickness?
Hi all,
I'd like to know boundary layer thickness around an airfoil (for ex. NACA 0012), I can use http://www.mhaerotools.de/airfoils/javafoil.htm but the only result it can display are: v/V: normalized surface velocity d1: displacement thickness d2: momentum loss thickness d3: energy loss thickness Cfl: ocal friction coefficient H12: shape factor d1/d2 H32: shape factor d3/d2 flow state: laminar, turbulent, separated y1: the first cell height required for y+=1 (multiplied by 100 resp. in %) value useful for grid generation how can I calculate Boundary Layer thickness from any of these quantities? or is there a semiempirical formula to calculate it for an airfoil like the one posted above? δ=5.2x/√Re 
up; maybe I should have opened another topic

All times are GMT 4. The time now is 13:09. 