Simulating NACA 2412 Airfoil over Varied Angles of Attack in Ansys Fluent with Verification
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Күн бұрынVideo builds on work by Cillian Thomas:
• NACA2412 Tutorial in A...
Video builds on work by Anthony T:
• ANSYS Fluent NACA 4412...
We show how to create a simple table of design points with a set of appropriate x- and y- velocities for inputs across angles of attack going from -8 degrees to +18 degrees for an inlet velocity of 33 m/s and Reynolds number of 2.2 million. We also use simple calculations of appropriate resultant forces to make sure we are determining a drag force parallel to the flow and a lift force normal to the flow. The simulated coefficients of lift and drag are in reasonable alignment with experimental data.
@iamSR007 4 ай бұрын
Sir , Thank You. Can you kindly share the files, especially the matlab plot codes and all🥰🥰
@emredemir229 3 ай бұрын
Thank you for the very well description. I have a question how you can be sure that the same iteration number is OK for all angles? I am not quite sure that the simulation can be converged with 1000 iterations for 12-14-16 degres.
@ersahguloglu2577 4 ай бұрын
Hey I want to do an analysis for supercritical airfoil. Is this set up options are okay for that or should I change some options if yes what are they? Could you help me with that?
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