ransfoil.configcpt

Input a name of airfoil coordinates file(1D XYZ/CPT):
'cases/NACA001264.cpt'
Using control points based parametric spline(Y/N)?
Y
Select air property(com/incom):
incom
Solve Energy equation(Y/N)?
Y
Include Viscous Heating(Y/N)?
N
Select turbulence model(inv/lam/sa/ke/sst):
sst
Select wall treatment method(wf/lr):
wf
Select coupling method(SIMPLE/SIMPLEC):
SIMPLE
Select discretization scheme(1upwind/2upwind/Quick/tvd):
2upwind
Select type of linear solver for convective-diffusion equations(sor/pbicg):
sor
Set boundary condition type of tempreture(fixed/flux):
fixed
Initialize from a file(Y/N)?
N
Initialize using stagnation values(Y/N)? (or Input a filename for initialization:)
N
Input maximum iteration steps:
2000
Input minimum residual of iteration:
1e-5
Input relaxation factor of velocity:
7e-1
Input relaxation factor of pressure:
3e-1
Input relaxation factor of temperature:
7e-1
Input relaxation factor of turbulence:
7e-1
Input number of grid points on whole airfoil(interpolation based on parametric spline):
201
Input dimensionless mesh spacing near leading edge:
5e-4
Input dimensionless mesh spacing near trailing edge:
5e-3
Input dimensionless near wall mesh spacing:
1e-3
Input layers of uniform near wall mesh:
5
Input total number of grid points normal to the airfoil surface:
75
Input chord length(m):
0.5334
Input velocity of free stream(m/s):
75
Input angle of attack(deg):
4
Input temperature of free stream(K):
263.15
Input temperature of wall(K):
273.15
Input ambient pressure(Pa):
100000
Input turbulent viscosity ratio of free stream:
1e-2
Input turbulent viscosity ratio of free stream:
10
Input wall roughness(m):
0
Input a directory of export files:
cases