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Winfoil Airfoils - Total Number: 277
Name T/C % T/C % Chord Position Camber % Camber Chord % CL Max CD Min
<< First < Prev 33 34 35 36 37 Next > Last >>
NACA 6409 9.04 50 5.973 40 1.383 0
NACA 6412 12.06 50 5.981 40 1.535 0.0075
NACA 64A210 9.97 39.96 1.325 49.99 0.558 0.0004
NACA 64A-312 11.95 38.26 1.554 51.68 1.059 0.009
NACA 64A410 9.96 38.26 2.115 51.68 1.065 0.0009
Coordinates
XUpper YUpper XLower YLower
0 0 0 0
0.1 0.3 0.1 -0.15
0.2 0.5 0.2 -0.2
0.3 0.7 0.3 -0.3
0.4 0.8 0.4 -0.4
0.5 1 0.5 -0.5
1 1.6 1 -0.7
1.5 2 1.5 -0.9
2 2.4 2 -1
2.5 2.96 2.5 -1.11
5 4.3 5 -1.18
7.5 5.42 7.5 -1.08
10 6.31 10 -0.88
15 7.78 15 -0.36
20 8.88 20 0.17
25 9.58 25 0.7
30 10.13 30 1.12
40 10.35 40 1.65
50 9.81 50 1.86
60 8.78 60 1.92
70 7.28 70 1.76
80 5.34 80 1.36
90 2.95 90 0.74
100 0 100 0
X Y
1 0
0.9 0.0295
0.8 0.0534
0.7 0.0728
0.6 0.0878
0.5 0.0981
0.4 0.1035
0.3 0.1013
0.25 0.0958
0.2 0.0888
0.15 0.0778
0.1 0.0631
0.075 0.0542
0.05 0.043
0.025 0.0296
0.02 0.024
0.015 0.02
0.01 0.016
0.005 0.01
0.004 0.008
0.003 0.007
0.002 0.005
0.001 0.003
0 0
0 0
0.001 -0.0015
0.002 -0.002
0.003 -0.003
0.004 -0.004
0.005 -0.005
0.01 -0.007
0.015 -0.009
0.02 -0.01
0.025 -0.0111
0.05 -0.0118
0.075 -0.0108
0.1 -0.0088
0.15 -0.0036
0.2 0.0017
0.25 0.007
0.3 0.0112
0.4 0.0165
0.5 0.0186
0.6 0.0192
0.7 0.0176
0.8 0.0136
0.9 0.0074
1 0
X Y
100 0
90 2.95
80 5.34
70 7.28
60 8.78
50 9.81
40 10.35
30 10.13
25 9.58
20 8.88
15 7.78
10 6.31
7.5 5.42
5 4.3
2.5 2.96
2 2.4
1.5 2
1 1.6
0.5 1
0.4 0.8
0.3 0.7
0.2 0.5
0.1 0.3
0 0
0 0
0.1 -0.15
0.2 -0.2
0.3 -0.3
0.4 -0.4
0.5 -0.5
1 -0.7
1.5 -0.9
2 -1
2.5 -1.11
5 -1.18
7.5 -1.08
10 -0.88
15 -0.36
20 0.17
25 0.7
30 1.12
40 1.65
50 1.86
60 1.92
70 1.76
80 1.36
90 0.74
100 0
V 1.1