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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 24 25 26 27 28 Next > Last >>
NACA 2410 10.01 29.88 1.963 40 1.045 0.0091
NACA 2408 8.01 29.9 1.97 40 0.866 0.0068
NACA 23021 20.95 30 1.846 10 1.121 0.0046
NACA 23018 17.96 30 1.835 15 1.275 0.0132
NACA 23015 14.97 30 1.831 15 1.48 0.0116
Coordinates
XUpper YUpper XLower YLower
0 0 0 0
0.25 0.7 0.25 -0.5
0.5 1.1 0.5 -0.8
1 1.55 1 -1.25
1.1 1.69 1.4 -1.45
2.3 2.41 2.7 -1.93
7.22 4.17 7.78 -2.81
9.71 4.77 10.29 -3.02
14.72 5.67 15.28 -3.23
19.76 6.28 20.24 -3.28
24.81 6.67 25.19 -3.23
29.88 6.88 30.13 -3.13
40 6.84 40 -2.84
50.05 6.36 49.95 -2.47
60.09 5.58 59.92 -2.02
70.1 4.55 69.9 -1.55
80.1 3.3 79.9 -1.55
90.07 1.82 89.93 -0.59
95.04 0.99 94.96 -0.35
100 0.11 100 -0.11
X Y
1 0.0011
0.9504 0.0099
0.9007 0.0182
0.801 0.033
0.701 0.0455
0.6009 0.0558
0.5005 0.0636
0.4 0.0684
0.2988 0.0688
0.2481 0.0667
0.1976 0.0628
0.1472 0.0567
0.0971 0.0477
0.0722 0.0417
0.023 0.0241
0.011 0.0169
0.01 0.0155
0.005 0.011
0.0025 0.007
0 0
0 0
0.0025 -0.005
0.005 -0.008
0.01 -0.0125
0.014 -0.0145
0.027 -0.0193
0.0778 -0.0281
0.1029 -0.0302
0.1528 -0.0323
0.2024 -0.0328
0.2519 -0.0323
0.3013 -0.0313
0.4 -0.0284
0.4995 -0.0247
0.5992 -0.0202
0.699 -0.0155
0.799 -0.0155
0.8993 -0.0059
0.9496 -0.0035
1 -0.0011
X Y
100 0.11
95.04 0.99
90.07 1.82
80.1 3.3
70.1 4.55
60.09 5.58
50.05 6.36
40 6.84
29.88 6.88
24.81 6.67
19.76 6.28
14.72 5.67
9.71 4.77
7.22 4.17
2.3 2.41
1.1 1.69
1 1.55
0.5 1.1
0.25 0.7
0 0
0 0
0.25 -0.5
0.5 -0.8
1 -1.25
1.4 -1.45
2.7 -1.93
7.78 -2.81
10.29 -3.02
15.28 -3.23
20.24 -3.28
25.19 -3.23
30.13 -3.13
40 -2.84
49.95 -2.47
59.92 -2.02
69.9 -1.55
79.9 -1.55
89.93 -0.59
94.96 -0.35
100 -0.11
V 1.1