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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 3 4 5 6 7 Next > Last >>
EPPLER 61 6.15 30 6.517 50 1.149 0.0005
AG12 6.23 20.8004 2.102 27.6418 0.878 0.0065
AG03 (flat aft bottom) 6.24 25.6511 2.013 31.8857 0.981 0.0076
AG04 6.42 21.8852 1.703 39.3636 0.931 0.0077
RAF 25 6.43 29.85 1.043 49.86 0.746 0.0043
Coordinates
XUpper YUpper XLower YLower
0 0.95 0 1.32
0.12 1.94 0.12 0.59
0.55 2.28 0.55 0.25
0.99 2.46 0.99 0.19
1.25 2.7 1.25 0
2.5 3.4 2.5 0.15
5 4.7 5 0.5
7.5 5.8 7.5 0.95
10 6.5 10 1.1
15 7.6 15 2
20 8.4 20 2.3
30 9.3 30 3.15
40 9.95 40 4
50 9.8 50 4.2
60 8.8 60 4.3
70 7.7 70 4
80 6 80 3.1
90 3.7 90 2
95 2.15 95 1
100 0 100 0
X Y
1 0
0.95 0.0215
0.9 0.037
0.8 0.06
0.7 0.077
0.6 0.088
0.5 0.098
0.4 0.0995
0.3 0.093
0.2 0.084
0.15 0.076
0.1 0.065
0.075 0.058
0.05 0.047
0.025 0.034
0.0125 0.027
0.0099 0.0246
0.0055 0.0228
0.0012 0.0194
0 0.0095
0 0.0132
0.0012 0.0059
0.0055 0.0025
0.0099 0.0019
0.0125 0
0.025 0.0015
0.05 0.005
0.075 0.0095
0.1 0.011
0.15 0.02
0.2 0.023
0.3 0.0315
0.4 0.04
0.5 0.042
0.6 0.043
0.7 0.04
0.8 0.031
0.9 0.02
0.95 0.01
1 0
X Y
100 0
95 2.15
90 3.7
80 6
70 7.7
60 8.8
50 9.8
40 9.95
30 9.3
20 8.4
15 7.6
10 6.5
7.5 5.8
5 4.7
2.5 3.4
1.25 2.7
0.99 2.46
0.55 2.28
0.12 1.94
0 0.95
0 1.32
0.12 0.59
0.55 0.25
0.99 0.19
1.25 0
2.5 0.15
5 0.5
7.5 0.95
10 1.1
15 2
20 2.3
30 3.15
40 4
50 4.2
60 4.3
70 4
80 3.1
90 2
95 1
100 0
V 1.1