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December 14, 2021, 00:12
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Cd does not converge to published value
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#1 |
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New Member
Join Date: Nov 2021
Posts: 4
Rep Power: 4  |
I am flowing a (1m) NACA 2412 airfoil to which the Cl has converged on correct published values. Yet, the drag coefficient is not, and maintains a 5.75x -> 6.00x difference through different alpha profiles. What am I doing wrong here? Thanks in advance.
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December 14, 2021, 06:46
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#2 | |
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Senior Member
Chaotic Water
Join Date: Jul 2012
Location: Elgrin Fau
Posts: 436
Rep Power: 17 |
Quote:
In general drag is mostly viscous - so you might not be resolving well enough the boundary layer, including transition. |
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