[moons2001]

we carry out cfd about wing
we ask you for finding problems
problem 1 - As aoa is more and more big, continuity don't well drop
less than 1e-2
we think because of the problem of grid and viscours model
but we don't find a effective solution

please we need your assistances!!!

below contents are cfd condition

cfd analysis model

airfoil naca0012
chord length 1m
span 10m
wing planforms rectangular

2-D arrayal grid D type model

we consider vortex effect to wing tip
so we give more volume to outside

analysis condition

re 3,000,000
mach 0.1288(43.8122m/s)

viscous model S-A model

solution control

pvc - simple
discretization - pressure - standard
momentum - first order upwind
modified turbulent viscosity - first order upwind
energy - first order upwind

under relaxation factors
momentum 0.7
modified turbulent viscosity 0.7
turbulent viscosity 0.7
energy 0.7
rest default