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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 1 2 3 4 5 Next > Last >>
NACA 63-010 9.98 35 0 0 0.699 0.0065
EPPLER 184 8.31 32.12 1.146 36.76 0.7 0.005
NACA 66-209 8.98 44.99 1.109 50 0.722 0.0001
MH 22 7.2 28.86 1.89 33.42 0.725 0.0048
MH22 7.21 28.86 1.889 33.42 0.739 0.0041
Coordinates
XUpper YUpper XLower YLower
0 0 0 0
0.1 0.4 0.1 -0.4
0.25 0.6 0.25 -0.6
0.5 0.83 0.5 -0.83
0.75 1 0.75 -1
1.25 1.28 1.25 -1.28
2.5 1.76 2.5 -1.76
5 2.44 5 -2.44
7.5 2.95 7.5 -2.95
10 3.36 10 -3.36
15 3.99 15 -3.99
20 4.45 20 -4.45
25 4.75 25 -4.75
30 4.94 30 -4.94
35 5 35 -5
40 4.94 40 -4.94
45 4.77 45 -4.77
50 4.5 50 -4.5
55 4.14 55 -4.14
60 3.72 60 -3.72
65 3.23 65 -3.23
70 2.71 70 -2.71
75 2.17 75 -2.17
80 1.62 80 -1.62
85 1.09 85 -1.09
90 0.6 90 -0.6
95 0.21 95 -0.21
100 0 100 0
X Y
1 0
0.95 0.0021
0.9 0.006
0.85 0.0109
0.8 0.0162
0.75 0.0217
0.7 0.0271
0.65 0.0323
0.6 0.0372
0.55 0.0414
0.5 0.045
0.45 0.0477
0.4 0.0494
0.35 0.05
0.3 0.0494
0.25 0.0475
0.2 0.0445
0.15 0.0399
0.1 0.0336
0.075 0.0295
0.05 0.0244
0.025 0.0176
0.0125 0.0128
0.0075 0.01
0.005 0.0083
0.0025 0.006
0.001 0.004
0 0
0 0
0.001 -0.004
0.0025 -0.006
0.005 -0.0083
0.0075 -0.01
0.0125 -0.0128
0.025 -0.0176
0.05 -0.0244
0.075 -0.0295
0.1 -0.0336
0.15 -0.0399
0.2 -0.0445
0.25 -0.0475
0.3 -0.0494
0.35 -0.05
0.4 -0.0494
0.45 -0.0477
0.5 -0.045
0.55 -0.0414
0.6 -0.0372
0.65 -0.0323
0.7 -0.0271
0.75 -0.0217
0.8 -0.0162
0.85 -0.0109
0.9 -0.006
0.95 -0.0021
1 0
X Y
100 0
95 0.21
90 0.6
85 1.09
80 1.62
75 2.17
70 2.71
65 3.23
60 3.72
55 4.14
50 4.5
45 4.77
40 4.94
35 5
30 4.94
25 4.75
20 4.45
15 3.99
10 3.36
7.5 2.95
5 2.44
2.5 1.76
1.25 1.28
0.75 1
0.5 0.83
0.25 0.6
0.1 0.4
0 0
0 0
0.1 -0.4
0.25 -0.6
0.5 -0.83
0.75 -1
1.25 -1.28
2.5 -1.76
5 -2.44
7.5 -2.95
10 -3.36
15 -3.99
20 -4.45
25 -4.75
30 -4.94
35 -5
40 -4.94
45 -4.77
50 -4.5
55 -4.14
60 -3.72
65 -3.23
70 -2.71
75 -2.17
80 -1.62
85 -1.09
90 -0.6
95 -0.21
100 0
V 1.1