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Winfoil Airfoils - Total Number: 277
Name T/C % Camber % Camber Chord % CL Max CD Min
1 2 3 4 5 Next > Last >>
B-29 ROOT 21.92 1.782 39.94 1.699 0.0333
NACA 654-221 20.98 1.113 50 0.646 0.0123
NACA 664-221 20.98 1.119 50 1.434 0.008
NACA 23021 20.95 1.846 10 1.121 0.0046
NACA 0219 18.99 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
V 1.0