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June 9, 2014, 05:48 |
NACA6409 results
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#1 |
New Member
Samir
Join Date: Jun 2014
Posts: 4
Rep Power: 11 |
Hey , I've been working on the airfoil NACA 6409. The Cl value which i got is 0.67725 and Cd is 0.0098 . Can anyone tell me if these values are okay for reynold's number 3 million and inlet velocity 43.84 m/s. Thanks
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