|April 26, 2009, 16:59||
Solid Airfoil Analysi (Stagnation vs Static Temp)
Join Date: Apr 2009
Posts: 2Rep Power: 0
Hi I am modelling a solid airfoil, usig ideal gas equation, mach number = 0.85, second order discretization, sutherland law (for viscosity), viscous heating on.
Now I am interested in the temperatures inside the airfoil, and not on the surface.
I am setting up a single boundary condition -pressure afar, with press =20980 and and angle of attack of 3 and a temp = 216.7 K.
I am getting a result, stating that the inside temperature is = to the stagnant temperature.
I have checked for grid independency, residuals and converge and all seems to be ok.
Has anyone any idea, or come arcoss literature that might confirm my CFD analysis please?
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