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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 5 6 7 8 9 Next > Last >>
ATR 14.52 25.4 2.882 21.4 1.632 0.0092
EPPLER 340 13.69 30.36 2.617 22.2 1.184 0.0246
EPPLER 336 12.79 30.23 2.829 22.94 1.154 0.0198
KC-135 BL52.44 15.45 35 1.015 25 1.382 0.0079
MH29 13.6 40.94 1.626 26.59 0.97 0.0065
Coordinates
XUpper YUpper XLower YLower
0 -0.01 0 -0.01
0.09 0.63 0.45 -1.21
0.44 1.5 1.32 -1.92
0.93 2.28 1.66 -2.1
2.56 4.1 5.14 -3.15
3.38 4.8 9.15 -3.7
6.07 6.56 13 -3.99
8.2 7.58 15.7 -4.13
10.7 8.49 18.2 -4.23
13.1 9.13 21.5 -4.34
15.8 9.62 24.6 -4.42
19.1 9.97 26.8 -4.47
21.4 10.08 29.1 -4.5
25.4 10.08 32.1 -4.53
29.5 9.93 34.6 -4.52
33.8 9.68 37.6 -4.48
38.1 9.39 40.5 -4.42
40.5 9.2 43.4 -4.33
43.1 8.98 46 -4.25
45.8 8.73 48.7 -4.14
48.8 8.41 51.1 -4.04
51.7 8.05 53.2 -3.94
53.5 7.82 55.2 -3.84
55.6 7.54 57.2 -3.73
57.5 7.29 59.6 -3.59
59.8 6.98 62.4 -3.39
62.3 6.63 65 -3.2
64.9 6.25 68.2 -2.95
67 5.92 71.4 -2.7
69.6 5.51 74.3 -2.47
72.3 5.07 76.9 -2.27
75.1 4.59 79.6 -2.04
77.6 4.15 82.6 -1.76
80.5 3.62 85.4 -1.48
83 3.14 88.5 -1.14
85.9 2.57 91.6 -0.79
88.5 2.05 94.6 -0.46
91.4 1.48 97.9 -0.14
100 0 100 0
X Y
1 0
0.914 0.0148
0.885 0.0205
0.859 0.0257
0.83 0.0314
0.805 0.0362
0.776 0.0415
0.751 0.0459
0.723 0.0507
0.696 0.0551
0.67 0.0592
0.649 0.0625
0.623 0.0663
0.598 0.0698
0.575 0.0729
0.556 0.0754
0.535 0.0782
0.517 0.0805
0.488 0.0841
0.458 0.0873
0.431 0.0898
0.405 0.092
0.381 0.0939
0.338 0.0968
0.295 0.0993
0.254 0.1008
0.214 0.1008
0.191 0.0997
0.158 0.0962
0.131 0.0913
0.107 0.0849
0.082 0.0758
0.0607 0.0656
0.0338 0.048
0.0256 0.041
0.0093 0.0228
0.0044 0.015
0.0009 0.0063
0 -0.0001
0 -0.0001
0.0045 -0.0121
0.0132 -0.0192
0.0166 -0.021
0.0514 -0.0315
0.0915 -0.037
0.13 -0.0399
0.157 -0.0413
0.182 -0.0423
0.215 -0.0434
0.246 -0.0442
0.268 -0.0447
0.291 -0.045
0.321 -0.0453
0.346 -0.0452
0.376 -0.0448
0.405 -0.0442
0.434 -0.0433
0.46 -0.0425
0.487 -0.0414
0.511 -0.0404
0.532 -0.0394
0.552 -0.0384
0.572 -0.0373
0.596 -0.0359
0.624 -0.0339
0.65 -0.032
0.682 -0.0295
0.714 -0.027
0.743 -0.0247
0.769 -0.0227
0.796 -0.0204
0.826 -0.0176
0.854 -0.0148
0.885 -0.0114
0.916 -0.0079
0.946 -0.0046
0.979 -0.0014
1 0
X Y
100 0
91.4 1.48
88.5 2.05
85.9 2.57
83 3.14
80.5 3.62
77.6 4.15
75.1 4.59
72.3 5.07
69.6 5.51
67 5.92
64.9 6.25
62.3 6.63
59.8 6.98
57.5 7.29
55.6 7.54
53.5 7.82
51.7 8.05
48.8 8.41
45.8 8.73
43.1 8.98
40.5 9.2
38.1 9.39
33.8 9.68
29.5 9.93
25.4 10.08
21.4 10.08
19.1 9.97
15.8 9.62
13.1 9.13
10.7 8.49
8.2 7.58
6.07 6.56
3.38 4.8
2.56 4.1
0.93 2.28
0.44 1.5
0.09 0.63
0 -0.01
0 -0.01
0.45 -1.21
1.32 -1.92
1.66 -2.1
5.14 -3.15
9.15 -3.7
13 -3.99
15.7 -4.13
18.2 -4.23
21.5 -4.34
24.6 -4.42
26.8 -4.47
29.1 -4.5
32.1 -4.53
34.6 -4.52
37.6 -4.48
40.5 -4.42
43.4 -4.33
46 -4.25
48.7 -4.14
51.1 -4.04
53.2 -3.94
55.2 -3.84
57.2 -3.73
59.6 -3.59
62.4 -3.39
65 -3.2
68.2 -2.95
71.4 -2.7
74.3 -2.47
76.9 -2.27
79.6 -2.04
82.6 -1.76
85.4 -1.48
88.5 -1.14
91.6 -0.79
94.6 -0.46
97.9 -0.14
100 0
V 1.1