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Old   March 25, 2020, 20:24
Default Naca 0012
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anson
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Hi,

am new to CFD here. Please bear with me.

What I have completed is the research for various angles for NACA 0012 foil; at 0, 5 and 10 degrees. As you can see in the results, the results indicates as given:

-4 drag and 0 lift at 0 degrees
-3 drag and 98 lift at 5 degrees
-10 drag and 197 lift at 10 degrees



I do not understand this trend. However, I do know that part of the reasoning has to do with lift and drag and even velocity. What is the explanation behind this trend?

Please advise if my results are wrong too. Any suggestion will help in a big way. Gladly appreciate your generous help.

Warmest Regards
Anson T
Attached Images
File Type: jpg 0 degrees drag and lift.jpg (98.6 KB, 12 views)
File Type: jpg 5 degrees drag and lift.jpg (99.7 KB, 12 views)
File Type: jpg 10 degrees drag and lift.jpg (103.4 KB, 11 views)
File Type: gif different angles of foil lift and drag.gif (30.0 KB, 13 views)
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Old   March 31, 2020, 03:06
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Burut
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you get the correct values if you build a graph of CL by AOA and compare it with your NASA to see for yourself.
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Old   March 31, 2020, 03:09
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My apologies. What does CL and AOA stand for?
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Old   March 31, 2020, 04:10
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Quote:
Originally Posted by Manucher View Post
you get the correct values if you build a graph of CL by AOA and compare it with your NASA to see for yourself.
My apologies. What does CL and AOA stand for?
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Old   March 31, 2020, 04:38
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AOA is:
https://www.skybrary.aero/index.php/...of_Attack_(AOA)
Cl is:
https://en.wikipedia.org/wiki/Lift_coefficient
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