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Winfoil Airfoils - Total Number: 277
Name T/C % Camber % Camber Chord % CL Max CD Min
<< First < Prev 15 16 17 18 19 Next > Last >>
NACA 664-221 20.98 1.119 50 1.434 0.008
NACA 663-418 17.98 2.216 50 1.394 0.0076
NACA 663-218 17.97 1.117 50 1.166 0.0073
NACA 662-415 14.99 2.217 50 0.751 0.0001
NACA 662-215 14.98 1.109 50 0.915 0.0002
Coordinates
XUpper YUpper XLower YLower
0 0 0 0
0.1 1 0.1 -0.5
0.2 1.25 0.2 -0.8
0.37 1.57 0.63 -1.47
0.61 1.87 0.89 -1.73
1.1 2.34 1.41 -2.13
2.32 3.23 2.68 -2.85
4.8 4.58 5.2 -3.95
7.29 5.65 7.71 -4.81
9.79 6.57 10.21 -5.53
14.8 8.04 15.2 -6.69
19.82 9.17 20.19 -7.58
24.84 10.05 25.16 -8.26
29.87 10.71 30.13 -8.77
34.9 11.18 35.1 -9.12
39.93 11.48 40.07 -9.34
44.97 11.6 45.03 -9.4
50 11.54 50 -9.33
55.03 11.28 54.97 -9.09
60.06 10.76 59.94 -8.62
65.09 9.82 64.91 -7.76
70.1 8.58 69.9 -6.64
75.11 7.15 74.89 -5.36
80.11 5.59 79.89 -4
85.09 4 84.91 -2.65
90.07 2.44 89.93 -1.41
95.03 1.03 94.97 -0.4
100 0 100 0
V 1.0