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Winfoil Airfoils - Total Number: 277
Name T/C % Camber % Camber Chord % CL Max CD Min
<< First < Prev 16 17 18 19 20 Next > Last >>
NACA 66-210 10 1.105 50 0.808 0
NACA 66-209 8.98 1.109 50 0.722 0.0001
NACA 66-206 6 1.107 50 0.688 0.0003
NACA 661-212 12 1.111 50 0.986 0.0011
NACA 65A-410 9.97 2.125 50 1.032 0.007
Coordinates
XUpper YUpper XLower YLower
0 0 0 0
0.1 0.4 0.1 -0.3
0.2 0.5 0.2 -0.4
0.3 0.7 0.3 -0.55
0.44 0.81 0.56 -0.71
0.68 0.98 0.82 -0.84
1.17 1.25 1.33 -1.03
2.41 1.7 2.59 -1.33
4.9 2.4 5.1 -1.77
7.4 2.96 7.6 -2.11
9.9 3.43 10.1 -2.39
14.9 4.2 15.1 -2.86
19.91 4.8 20.09 -3.2
24.92 5.26 25.08 -3.47
29.94 5.61 30.06 -3.66
34.95 5.86 35.05 -3.8
39.97 6.02 40.03 -3.88
44.98 6.1 45.02 -3.91
50 6.07 50 -3.87
55.02 5.96 54.98 -3.77
60.03 5.74 59.97 -3.59
65.04 5.33 64.96 -3.27
70.05 4.76 69.95 -2.82
75.06 4.07 74.94 -2.28
80.06 3.29 79.94 -1.7
85.05 2.45 84.95 -1.1
90.04 1.57 89.96 -0.54
95.02 0.72 94.98 -0.09
100 0 100 0
V 1.0