Simpliest way to run airfoil simulation diff AOA
i need to simulate a naca0012 airfoil at different AOA at Re=2000. what's the fastest way of doing it. I wonder if i can rotate the whole grid at different AOA to do it. The BC at inlet is just kept at u=1. Is it possible?
btw, I used to fix the grid and modify the inlet velocity to their components ie at AOA=7deg, u=1*cos(7), v=1*sin(7). I also changed the force calculation to x=1*cos(7),v=1*sin(7) for drag and the opposite for lift
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