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Winfoil Airfoils - Total Number: 277
Name T/C % Camber % Camber Chord % CL Max CD Min
<< First < Prev 44 45 46 47 48 Next > Last >>
CLARK Y 11.73 3.528 43.47 1.595 0.006
CLARK W 11.21 3.684 40 1.643 0.0075
CLARK V 11.6 3.355 50 1.617 0.0074
CLARK K 11.38 3.245 39.65 1.676 0.0066
BOEING-VERTOL VR-1 10.95 1.542 43.33 1.121 0.0059
Coordinates
XUpper YUpper XLower YLower
0 0.05 0 0.05
0.11 0.62 0.11 -0.45
0.43 1.25 0.43 -0.9
0.96 1.94 0.96 -1.3
1.7 2.65 1.7 -1.65
2.65 3.35 2.65 -1.96
3.81 4.03 3.81 -2.21
5.16 4.68 5.16 -2.41
6.7 5.31 6.7 -2.57
8.43 5.94 8.43 -2.68
10.33 6.55 10.33 -2.76
12.41 7.13 12.41 -2.82
14.65 7.66 14.65 -2.84
17.03 8.11 17.03 -2.83
19.56 8.48 19.56 -2.8
22.22 8.77 22.22 -2.73
25 9 25 -2.65
27.89 9.16 27.89 -2.56
30.87 9.27 30.87 -2.46
33.93 9.32 33.93 -2.35
37.06 9.31 37.06 -2.24
43.47 9.13 43.47 -2.02
50 8.72 50 -1.79
56.53 8.11 56.53 -1.57
62.94 7.32 62.94 -1.35
69.13 6.41 69.13 -1.13
75 5.41 75 -0.93
80.44 4.39 80.44 -0.74
85.36 3.4 85.36 -0.58
89.67 2.48 89.67 -0.43
93.3 1.66 93.3 -0.3
96.19 0.97 96.19 -0.19
98.3 0.45 98.3 -0.09
99.57 0.12 99.57 -0.03
100 0 100 0
V 1.0