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Winfoil Airfoils - Total Number: 277
Name T/C % Camber % Camber Chord % CL Max CD Min
1 2 3 4 5 Next > Last >>
A18 (original) 7.33 3.939 45 1.1 0.0069
AG 10 10 6.443 32.1 1.798 0.015
AG 27 6.11 2.666 44.2161 1.066 0.0073
AG 34 9.28 2.485 36.863 1.236 0.0103
AG 35 8.72 2.341 35.6838 1.124 0.0099
Coordinates
XUpper YUpper XLower YLower
0 1.49 0 1.49
0.23 2.4 0.23 1.14
0.91 2.97 0.91 1.03
1.25 3.1673 1.25 0.78
2.5 3.95 2.5 0.36
5 4.92 5 0.08
7.5 5.66 7.5 0
10 6.23 10 0.01
15 7.03 15 0.2
20 7.6 20 0.48
25 8.07 25 0.81
30 8.38 30 1.04
35 8.47 35 1.35
40 8.38 40 1.66
45 8.29 45 1.78
50 7.98 50 1.88
55 7.61 55 1.98
60 7.2 60 2
70 6.06 70 1.92
80 4.62 80 1.45
90 2.86 90 0.81
95 1.82 95 0.43
100 0.61 100 0
X Y
1 0.0061
0.95 0.0182
0.9 0.0286
0.8 0.0462
0.7 0.0606
0.6 0.072
0.55 0.0761
0.5 0.0798
0.45 0.0829
0.4 0.0838
0.35 0.0847
0.3 0.0838
0.25 0.0807
0.2 0.076
0.15 0.0703
0.1 0.0623
0.075 0.0566
0.05 0.0492
0.025 0.0395
0.0125 0.031673
0.0091 0.0297
0.0023 0.024
0 0.0149
0 0.0149
0.0023 0.0114
0.0091 0.0103
0.0125 0.0078
0.025 0.0036
0.05 0.0008
0.075 0
0.1 0.0001
0.15 0.002
0.2 0.0048
0.25 0.0081
0.3 0.0104
0.35 0.0135
0.4 0.0166
0.45 0.0178
0.5 0.0188
0.55 0.0198
0.6 0.02
0.7 0.0192
0.8 0.0145
0.9 0.0081
0.95 0.0043
1 0
X Y
100 0.61
95 1.82
90 2.86
80 4.62
70 6.06
60 7.2
55 7.61
50 7.98
45 8.29
40 8.38
35 8.47
30 8.38
25 8.07
20 7.6
15 7.03
10 6.23
7.5 5.66
5 4.92
2.5 3.95
1.25 3.1673
0.91 2.97
0.23 2.4
0 1.49
0 1.49
0.23 1.14
0.91 1.03
1.25 0.78
2.5 0.36
5 0.08
7.5 0
10 0.01
15 0.2
20 0.48
25 0.81
30 1.04
35 1.35
40 1.66
45 1.78
50 1.88
55 1.98
60 2
70 1.92
80 1.45
90 0.81
95 0.43
100 0
V 1.1