Hi,

I need to generate grid which are fine enough to capture the boundary layer for my laminar external airfoil flow. Then I'm going to use my 2D FVM NS solver to get the solutions.

Is this way correct?:

1 use flat plate approximation formula of Blasius ie delta y (boundary layer thickness) = 5*x/sqrt(Re), x=characteristic length.

2. knowing my problem's Re, I can get delta y.

3 assumming I'm using 20 pts to capture the boundary layer, each grid spacing is delta y/20.

4. hence, i generate a grid whereby there's 20 rectangular cells of equal thickness of delta y/20 away from the airfoil wall. after that, the cells' thickness increases to reduce the no. of cells required.

Is this a reasonable way to capture the boundary layer accurately?

Thanks!

For Laminar flows, this is reasonable way; this is how I also generate laminar grids.

I'm simulating flow about airfoil. With grid generation technic I'm solving NS equations over a domain of radius 20xchord.But i don't give any particular treatment to the boundary layer zone.

Even in the boundary layer you can enlarge the normal grid spacing using a stretching function.

so is there any optimal spacing no. for the boundary layer? most of the time i see ppl using around 30. is this the same for different RE no.? At higher Re (5e3 - 5e4), must the spacing no. for increased?

btw, enlarging the grid spacing with a stretching function may make the computation more accurate but the matrix will take a longer time to solve.

Have a look at the following book: Boundary Layer Analysis by Joseph A. Schetz. It has a collection of FORTRAN codes to solve this and other Boundary Layer problems, he used 50 nodes in a case similar to yours Wish you nice reading