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October 18, 2013, 06:07 |
Need Cl,Cd for high angles of attack
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#1 |
New Member
dynamic
Join Date: Oct 2013
Posts: 3
Rep Power: 12 |
Hi
I am a final year student working on numerical modelling of Darrieus turbine. I require Cl,Cd as a function of angle of attack for angles - 0 to 60 deg. Can you please direct me to a source where I can find experimental/any reliable Cl Cd values for some symmetric NACA profiles. |
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October 23, 2013, 13:44 |
UIUC airfoil database
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#2 |
New Member
Muhammad Maaz Siddiqui
Join Date: Jun 2013
Location: Karachi, Pakistan
Posts: 3
Rep Power: 12 |
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October 24, 2013, 00:01 |
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#3 |
New Member
dynamic
Join Date: Oct 2013
Posts: 3
Rep Power: 12 |
Thanks for replying But I want Cl, Cd values of NACA airfoils for angles of attack 0-60 deg but I am finding results only for angles till 20deg and very few for NACA...Can u help?
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