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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 23 24 25 26 27 Next > Last >>
NACA 4412 12.02 30 3.943 40 1.649 0.0029
NACA 4403 3.03 34.5328 3.971 42.2134 0.896 0.0051
NACA 2418 17.96 30 1.95 40 1.367 0.0128
NACA 2415 14.97 30 1.954 40 1.328 0.0082
NACA 2412 11.98 30 1.96 40 1.178 0.0093
Coordinates
XUpper YUpper XLower YLower
0 0 0 0
0.25 0.9 0.25 -0.7
0.5 1.5 0.5 -1
1 2 1 -1.4
1.25 2.44 1.25 -1.43
2.5 3.39 2.5 -1.95
5 4.73 5 -2.49
7.5 5.76 7.5 -2.74
10 6.59 10 -2.86
15 7.89 15 -2.88
20 8.8 20 -2.74
25 9.41 25 -2.5
30 9.76 30 -2.26
40 9.8 40 -1.8
50 9.19 50 -1.4
60 8.14 60 -1
70 6.69 70 -0.65
80 4.89 80 -0.39
90 2.71 90 -0.22
95 1.47 95 -0.16
100 0.13 100 -0.13
X Y
1 0.0013
0.95 0.0147
0.9 0.0271
0.8 0.0489
0.7 0.0669
0.6 0.0814
0.5 0.0919
0.4 0.098
0.3 0.0976
0.25 0.0941
0.2 0.088
0.15 0.0789
0.1 0.0659
0.075 0.0576
0.05 0.0473
0.025 0.0339
0.0125 0.0244
0.01 0.02
0.005 0.015
0.0025 0.009
0 0
0 0
0.0025 -0.007
0.005 -0.01
0.01 -0.014
0.0125 -0.0143
0.025 -0.0195
0.05 -0.0249
0.075 -0.0274
0.1 -0.0286
0.15 -0.0288
0.2 -0.0274
0.25 -0.025
0.3 -0.0226
0.4 -0.018
0.5 -0.014
0.6 -0.01
0.7 -0.0065
0.8 -0.0039
0.9 -0.0022
0.95 -0.0016
1 -0.0013
X Y
100 0.13
95 1.47
90 2.71
80 4.89
70 6.69
60 8.14
50 9.19
40 9.8
30 9.76
25 9.41
20 8.8
15 7.89
10 6.59
7.5 5.76
5 4.73
2.5 3.39
1.25 2.44
1 2
0.5 1.5
0.25 0.9
0 0
0 0
0.25 -0.7
0.5 -1
1 -1.4
1.25 -1.43
2.5 -1.95
5 -2.49
7.5 -2.74
10 -2.86
15 -2.88
20 -2.74
25 -2.5
30 -2.26
40 -1.8
50 -1.4
60 -1
70 -0.65
80 -0.39
90 -0.22
95 -0.16
100 -0.13
V 1.1