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Winfoil Airfoils - Total Number: 277
Name T/C % T/C % Chord Position Camber % Camber Chord % CL Max CD Min
<< First < Prev 52 53 54 55 56 Next > Last >>
NACA 23018 17.96 30 1.835 15 1.275 0.0132
NACA 653-218 17.97 39.94 1.118 50 1.172 0.0034
NACA 653-418 17.97 39.88 2.221 50 1.41 0.0082
NACA 653-618 17.97 39.826 3.324 50 1.618 0.0085
NACA 663-218 17.97 44.97 1.117 50 1.166 0.0073
Coordinates
XUpper YUpper XLower YLower
0 0 0 0
0.3 2 0.3 -0.6
0.6 2.6 0.6 -1.1
1 3.5 1 -1.6
1.25 4.09 1.25 -1.83
2.5 5.29 2.5 -2.71
5 6.92 5 -3.8
7.5 8.01 7.5 -4.6
10 8.83 10 -5.22
15 9.86 15 -6.18
20 10.36 20 -6.86
25 10.56 25 -7.27
30 10.55 30 -7.47
40 10.04 40 -7.37
50 9.05 50 -6.81
60 7.75 60 -5.94
70 6.18 70 -4.82
80 4.4 80 -3.48
90 2.39 90 -1.94
95 1.32 95 -1.09
100 0.19 100 -0.19
X Y
1 0.0019
0.95 0.0132
0.9 0.0239
0.8 0.044
0.7 0.0618
0.6 0.0775
0.5 0.0905
0.4 0.1004
0.3 0.1055
0.25 0.1056
0.2 0.1036
0.15 0.0986
0.1 0.0883
0.075 0.0801
0.05 0.0692
0.025 0.0529
0.0125 0.0409
0.01 0.035
0.006 0.026
0.003 0.02
0 0
0 0
0.003 -0.006
0.006 -0.011
0.01 -0.016
0.0125 -0.0183
0.025 -0.0271
0.05 -0.038
0.075 -0.046
0.1 -0.0522
0.15 -0.0618
0.2 -0.0686
0.25 -0.0727
0.3 -0.0747
0.4 -0.0737
0.5 -0.0681
0.6 -0.0594
0.7 -0.0482
0.8 -0.0348
0.9 -0.0194
0.95 -0.0109
1 -0.0019
X Y
100 0.19
95 1.32
90 2.39
80 4.4
70 6.18
60 7.75
50 9.05
40 10.04
30 10.55
25 10.56
20 10.36
15 9.86
10 8.83
7.5 8.01
5 6.92
2.5 5.29
1.25 4.09
1 3.5
0.6 2.6
0.3 2
0 0
0 0
0.3 -0.6
0.6 -1.1
1 -1.6
1.25 -1.83
2.5 -2.71
5 -3.8
7.5 -4.6
10 -5.22
15 -6.18
20 -6.86
25 -7.27
30 -7.47
40 -7.37
50 -6.81
60 -5.94
70 -4.82
80 -3.48
90 -1.94
95 -1.09
100 -0.19
V 1.1