I want to find overall solution about wing cfd
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 |
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