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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 26 27 28 29 30 Next > Last >>
NACA 0009 8.97 30 0 0 0.871 0.0065
NACA 0010 9.97 30 0 0 0.877 0.0016
NACA 0012 11.96 30 0 0 1.108 0.0092
NACA 0015 15.01 28.73 0 0 1.287 0.0064
NACA 0016 15.91 27.3202 0 0 1.332 0.0106
Coordinates
XUpper YUpper XLower YLower
0 0 0 0
1.25 1.42 1.25 -1.42
2.5 1.96 2.5 -1.96
5 2.67 5 -2.67
7.5 3.15 7.5 -3.15
10 3.51 10 -3.51
15 4.01 15 -4.01
20 4.3 20 -4.3
25 4.46 25 -4.46
30 4.5 30 -4.5
40 4.35 40 -4.35
50 3.97 50 -3.97
60 3.42 60 -3.42
70 2.75 70 -2.75
80 1.97 80 -1.97
90 1.09 90 -1.09
95 0.61 95 -0.61
100 0.1 100 -0.1
X Y
1 0.001
0.95 0.0061
0.9 0.0109
0.8 0.0197
0.7 0.0275
0.6 0.0342
0.5 0.0397
0.4 0.0435
0.3 0.045
0.25 0.0446
0.2 0.043
0.15 0.0401
0.1 0.0351
0.075 0.0315
0.05 0.0267
0.025 0.0196
0.0125 0.0142
0 0
0 0
0.0125 -0.0142
0.025 -0.0196
0.05 -0.0267
0.075 -0.0315
0.1 -0.0351
0.15 -0.0401
0.2 -0.043
0.25 -0.0446
0.3 -0.045
0.4 -0.0435
0.5 -0.0397
0.6 -0.0342
0.7 -0.0275
0.8 -0.0197
0.9 -0.0109
0.95 -0.0061
1 -0.001
X Y
100 0.1
95 0.61
90 1.09
80 1.97
70 2.75
60 3.42
50 3.97
40 4.35
30 4.5
25 4.46
20 4.3
15 4.01
10 3.51
7.5 3.15
5 2.67
2.5 1.96
1.25 1.42
0 0
0 0
1.25 -1.42
2.5 -1.96
5 -2.67
7.5 -3.15
10 -3.51
15 -4.01
20 -4.3
25 -4.46
30 -4.5
40 -4.35
50 -3.97
60 -3.42
70 -2.75
80 -1.97
90 -1.09
95 -0.61
100 -0.1
V 1.1