solving aerofoil at an altitude
there are a lot of airfoils tutorial for sea level conditions but i could not find any to perform the analysis at an altitude .i tried a few cases i could not get the accurate result.
can anyone clarify the following conditions for me
operating pressure-absolute pressure at that altitude
temperature(constant in the boundry condition tab) -surrounding temp at the altitude
Sutherland law for viscosity -three co eff method (all 3 default constant)
reference values (from far-field)
the density value updates from the far-field for that altitude
the viscosity value remains default for sea level(i change it manually for the altitude)
solver-pressure -coupled -green guass node methord
can anyone identify the mistake im making?
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