Clark Y C81 table
Clark Y C81 table
(OP)
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.
-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
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RE: Clark Y C81 table
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: Eng-Tips.com Forum Policies http://eng-tips.com/market.cfm?
RE: Clark Y C81 table
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