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Winfoil Airfoils - Total Number: 277
Name T/C % Camber % Camber Chord % CL Max CD Min
<< First < Prev 1 2 3 4 5 Next > Last >>
NACA 63-010 9.98 0 0 0.699 0.0065
EPPLER 184 8.31 1.146 36.76 0.7 0.005
NACA 66-209 8.98 1.109 50 0.722 0.0001
MH 22 7.2 1.89 33.42 0.725 0.0048
MH22 7.21 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