help needed for swept back wing simulation
 

Hi all,

Can anyone tell me how to simulate a swept back wing in 2d process? I found the geometry of swept back airfoil using matlab code,but found absurd result after simulation. The experimental data of naca shows the stall at 34 degree but i got the stall before 20 degree for the airfoil. Is it possible in this way?

For incompressible (low speed subsonic) flow you can use XFLR5 (this software applies vortex lattice method in combination with drag polars from 2d sections).

thanks. is it possible in fluent using 2d airfoil?

i'm sorry but i might have missed something. what exactly do you mean 2d swept back wing?

as for your last post, yes in fluent it is possible to simulate a 2d profile, but remember that the stall is extreamely hard to catch.

EDIT: ok maybe i got it: you are talking about a profile deformed by the progection on the plane perpendicolar to the sweep.

just remember that a 2d profile assume an inifinte aspect ratio and discrad the 3d effects, wich might be quite significative, both for performance and stall angle, on a real geometry.