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Winfoil Airfoils - Total Number: 277
Name T/C % Camber % Camber Chord % CL Max CD Min
<< First < Prev 37 38 39 40 41 Next > Last >>
NACA 66-209 8.98 1.109 50 0.722 0.0001
NACA 66-210 10 1.105 50 0.808 0
NACA 662-215 14.98 1.109 50 0.915 0.0002
NACA 662-415 14.99 2.217 50 0.751 0.0001
NACA 663-218 17.97 1.117 50 1.166 0.0073
Coordinates
XUpper YUpper XLower YLower
0 0 0 0
0.1 0.4 0.1 -0.35
0.2 0.5 0.2 -0.4
0.3 0.65 0.3 -0.5
0.44 0.74 0.56 -0.64
0.69 0.89 0.81 -0.75
1.18 1.14 1.32 -0.92
2.42 1.55 2.58 -1.18
4.91 2.19 5.09 -1.56
7.41 2.71 7.59 -1.86
9.91 3.14 10.09 -2.11
14.91 3.85 15.09 -2.5
19.92 4.4 20.08 -2.8
24.93 4.82 25.07 -3.03
29.94 5.15 30.06 -3.2
34.96 5.38 35.04 -3.32
39.97 5.53 40.03 -3.39
44.99 5.59 45.01 -3.4
50 5.58 50 -3.37
55.01 5.48 54.99 -3.29
60.03 5.28 59.97 -3.13
65.04 4.91 64.96 -2.85
70.05 4.4 69.95 -2.46
75.05 3.77 74.95 -1.98
80.05 3.06 79.95 -1.47
85.04 2.28 84.96 -0.94
90.03 1.48 89.97 -0.44
95.02 0.69 94.98 -0.06
100 0 100 0
V 1.0