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How do I get exact Cp plot for NACA airfoil in Ansys fluent? |
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February 8, 2019, 10:41 |
How do I get exact Cp plot for NACA airfoil in Ansys fluent?
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New Member
Tanmay Bhise
Join Date: Feb 2019
Posts: 1
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I have done the simulation with C-type mesh(2.5million elements), steady state, K-w SST. My solution converged (Convergence criterion of 10e-06). But in my Cp vs X plot
I am getting an error of '+1'. I imported Cp co-ordinates into excel and added '+1' in each of the Cp value and Plotted graph again. This plot is matching with the original values. But why am I getting an error of '+1' in Fluent? Cp plot on fluent https://drive.google.com/file/d/123B...usp=drive_open Cp plot after adding '+1':https://drive.google.com/file/d/16Sr...usp=drive_open Original Cp plot by NASA: https://drive.google.com/file/d/1VkG...usp=drive_open Last edited by tanmaybhise; February 8, 2019 at 16:49. |
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Tags |
airfoil, cfd, fluent, naca, pressure coefficient |
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