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Help with NACA 0012 3D simulation

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Old   December 30, 2016, 06:40
Default Help with NACA 0012 3D simulation
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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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