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Clark Y C81 table

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GregLocock

GregLocock

Automotive
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Apr 10, 2001
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For obscure reasons I need the CL and CD tables for Clark Y at the following alphas

-180
-172.5
-161
-147
-129
-49
-39
-21
-16.5
-15
-14
-13
-12
-11
-10
-8
-6
-4
-2
0
2
4
6
8
10
11
12
13
14
15
16.5
21
39
49
129
147
161
172.5
180


and Mach numbers

0 0.2 0.3 0.4 0.5 0.6 0.7 0.75 0.8 0.9 1


Re is for a 100mm chord

I'm guessing XFOIL will do this.



Cheers

Greg Locock


New here? Try reading these, they might help FAQ731-376
 
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Well, I now have XFOIL, and the very useful matlab interface.

But sadly xfoil is no good for the ridiculous alpha figures, although having said that my rotor design doesn't use ridiculous alpha so i should be ok



Cheers

Greg Locock


New here? Try reading these, they might help FAQ731-376
 
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Greg,
If you're still after some high AoA figures, you can explore the subject of wind turbines a little and find data for common airfoils at ALL angles of attack.
Particularly the NREL that tried a few concept VAWT turbines back in the 70's. The reports are "googlable" but if your searches turn up dry, I have links and PDF's at home.




STF
 
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