[suresh1483]

Hi,
I am solving 3D euler equation on aircraft wing, I am using FVM in unstructured grid with cell centred method. I use Lax-Friedrich scheme to discretize the equation. My results are not correct, temperatures, pressure and density are higher than the stag. values at wall boundaries. I think my boundary conditions are wrong.

I am using a circular domain of 15 times of root chord as diameter, my BC are as follows,

Far field: Free stream values. (since the domain is circular, no seperate BC for inlet and exit)

Wall boundary: reflective velocity method is used for velocity, and pressure and temperature are extrapolated from boundary cell to ghost cell.

Can any one suggest me for solution?