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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 25 26 27 28 29 Next > Last >>
NACA 23012 11.97 30 1.835 15 1.173 0.0072
NACA 2213 12.93 27.3499 1.987 20.6285 1.452 0.0095
NACA 1412 11.98 29.93 0.966 40 1.037 0.007
NACA 1410 9.99 29.94 0.971 40 0.913 0.0044
NACA 1408 7.99 29.95 0.978 40 0.782 0.0067
Coordinates
XUpper YUpper XLower YLower
0 0 0 0
0.2 0.65 0.2 -0.55
0.5 1.55 0.5 -0.85
1 2.3 1 -1.15
1.25 2.67 1.25 -1.23
2.5 3.61 2.5 -1.71
5 4.91 5 -2.26
7.5 5.8 7.5 -2.61
10 6.43 10 -2.92
15 7.19 15 -3.5
20 7.5 20 -3.97
25 7.6 25 -4.28
30 7.55 30 -4.46
40 7.14 40 -4.48
50 6.41 50 -4.17
60 5.47 60 -3.67
70 4.36 70 -3
80 3.08 80 -2.16
90 1.68 90 -1.23
95 0.92 95 -0.7
100 0.13 100 -0.13
X Y
1 0.0013
0.95 0.0092
0.9 0.0168
0.8 0.0308
0.7 0.0436
0.6 0.0547
0.5 0.0641
0.4 0.0714
0.3 0.0755
0.25 0.076
0.2 0.075
0.15 0.0719
0.1 0.0643
0.075 0.058
0.05 0.0491
0.025 0.0361
0.0125 0.0267
0.01 0.023
0.005 0.0155
0.002 0.0065
0 0
0 0
0.002 -0.0055
0.005 -0.0085
0.01 -0.0115
0.0125 -0.0123
0.025 -0.0171
0.05 -0.0226
0.075 -0.0261
0.1 -0.0292
0.15 -0.035
0.2 -0.0397
0.25 -0.0428
0.3 -0.0446
0.4 -0.0448
0.5 -0.0417
0.6 -0.0367
0.7 -0.03
0.8 -0.0216
0.9 -0.0123
0.95 -0.007
1 -0.0013
X Y
100 0.13
95 0.92
90 1.68
80 3.08
70 4.36
60 5.47
50 6.41
40 7.14
30 7.55
25 7.6
20 7.5
15 7.19
10 6.43
7.5 5.8
5 4.91
2.5 3.61
1.25 2.67
1 2.3
0.5 1.55
0.2 0.65
0 0
0 0
0.2 -0.55
0.5 -0.85
1 -1.15
1.25 -1.23
2.5 -1.71
5 -2.26
7.5 -2.61
10 -2.92
15 -3.5
20 -3.97
25 -4.28
30 -4.46
40 -4.48
50 -4.17
60 -3.67
70 -3
80 -2.16
90 -1.23
95 -0.7
100 -0.13
V 1.1