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December 30, 2016, 05:40 |
Help with NACA 0012 3D simulation
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Join Date: Dec 2016
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Hi everyone,
I am a student from a polytechnic in Singapore, and as part of my final year project I need to work with FLUENT to extract coefficient of pressure results. I'd like to ask if anyone knows the reason why I cannot get cP=1 at the leading edge of the 0012 airfoil at 0 degrees. Attached is the coefficient of pressure plot for the airfoil from the simulation I have done. My mesh specifications are as follows: Advanced Size: On: Curvature Relevance Center: Medium Initial Size Seed: Full Assembly (I've tried Active Assembly and the results are the same) Smoothing: High Span Angle Center: Fine Curvature: Default: 18 degrees Min Size: 1.2506e-003m Max Face Size: 5e-002 Max Size: 5e-002 Growth Rate: 1.050 Please feel free to provide comments and advice. Help is appreciated! Thanks! |
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fluent 16.0, help needed, naca 0012 |
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