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Winfoil Airfoils - Total Number: 277
Name T/C % T/C % Chord Position Camber % Camber Chord % CL Max CD Min
1 2 3 4 5 Next > Last >>
B-29 ROOT 21.92 29.94 1.782 39.94 1.699 0.0333
NACA 654-221 20.98 39.93 1.113 50 0.646 0.0123
NACA 664-221 20.98 44.97 1.119 50 1.434 0.008
NACA 23021 20.95 30 1.846 10 1.121 0.0046
NACA 0219 18.99 28.73 0 0 1.427 0.013
Coordinates
XUpper YUpper XLower YLower
0 0 0 0
0.83 2.33 0.61 -2.09
1.32 2.98 0.62 -2.1
2.56 4.25 0.88 -2.47
5.04 6.03 1.38 -3.07
7.52 7.39 2.64 -4.16
10.01 8.5 5.15 -5.48
14.98 10.23 7.66 -6.37
19.97 11.49 10.16 -7.03
24.95 12.3 15.17 -8.01
29.94 12.72 20.17 -8.69
39.94 12.53 25.17 -9.1
49.94 11.3 30.16 -9.26
59.95 9.34 40.15 -9.05
69.96 6.95 50.13 -8.34
79.98 4.45 60.11 -7.28
89.99 2.07 70.09 -5.91
95 0.98 80.06 -4.28
100 0 90.03 -2.35
X Y
1 0
0.95 0.0098
0.8999 0.0207
0.7998 0.0445
0.6996 0.0695
0.5995 0.0934
0.4994 0.113
0.3994 0.1253
0.2994 0.1272
0.2495 0.123
0.1997 0.1149
0.1498 0.1023
0.1001 0.085
0.0752 0.0739
0.0504 0.0603
0.0256 0.0425
0.0132 0.0298
0.0083 0.0233
0 0
0 0
0.0061 -0.0209
0.0062 -0.021
0.0088 -0.0247
0.0138 -0.0307
0.0264 -0.0416
0.0515 -0.0548
0.0766 -0.0637
0.1016 -0.0703
0.1517 -0.0801
0.2017 -0.0869
0.2517 -0.091
0.3016 -0.0926
0.4015 -0.0905
0.5013 -0.0834
0.6011 -0.0728
0.7009 -0.0591
0.8006 -0.0428
0.9003 -0.0235
X Y
100 0
95 0.98
89.99 2.07
79.98 4.45
69.96 6.95
59.95 9.34
49.94 11.3
39.94 12.53
29.94 12.72
24.95 12.3
19.97 11.49
14.98 10.23
10.01 8.5
7.52 7.39
5.04 6.03
2.56 4.25
1.32 2.98
0.83 2.33
0 0
0 0
0.61 -2.09
0.62 -2.1
0.88 -2.47
1.38 -3.07
2.64 -4.16
5.15 -5.48
7.66 -6.37
10.16 -7.03
15.17 -8.01
20.17 -8.69
25.17 -9.1
30.16 -9.26
40.15 -9.05
50.13 -8.34
60.11 -7.28
70.09 -5.91
80.06 -4.28
90.03 -2.35
V 1.1