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Winfoil Airfoils - Total Number: 277
Name T/C % Camber % Camber Chord % CL Max CD Min
<< First < Prev 49 50 51 52 53 Next > Last >>
S8036 (16%) 16 1.821 36.848 1.538 0.0054
S8037 15.98 2.431 36.9 1.574 0.005
SA7035 9.19 2.654 38.24 1.189 0.0058
SA7036 9.19 2.877 42.08 1.213 0.0062
SA7038 9.19 3.292 42.48 1.274 0.0056
Coordinates
XUpper YUpper XLower YLower
0.001 0.054 0.001 0.054
0.193 0.823 0.098 -0.588
0.612 1.649 0.548 -1.153
1.256 2.483 1.338 -1.72
2.141 3.305 2.433 -2.273
3.271 4.115 3.811 -2.804
4.638 4.885 5.468 -3.304
6.251 5.61 7.395 -3.773
8.104 6.296 9.576 -4.208
10.184 6.934 11.999 -4.605
12.484 7.52 14.648 -4.964
14.988 8.053 17.504 -5.283
17.681 8.528 20.549 -5.558
20.545 8.939 23.76 -5.786
23.564 9.28 27.12 -5.962
26.722 9.547 30.609 -6.084
29.999 9.735 34.204 -6.146
33.38 9.838 37.887 -6.147
36.848 9.853 41.638 -6.087
40.381 9.776 45.435 -5.959
43.972 9.598 49.265 -5.765
47.611 9.328 53.099 -5.502
51.279 8.963 56.937 -5.165
54.969 8.509 60.778 -4.772
58.668 7.986 64.594 -4.348
62.357 7.402 68.359 -3.907
66.022 6.771 72.043 -3.464
69.641 6.119 75.616 -3.028
73.183 5.463 79.048 -2.609
76.618 4.816 82.309 -2.215
79.916 4.189 85.37 -1.852
83.047 3.59 88.202 -1.523
85.984 3.027 90.775 -1.23
88.697 2.505 93.064 -0.97
91.163 2.027 95.044 -0.739
93.354 1.594 96.698 -0.519
95.247 1.204 98.037 -0.302
96.827 0.843 99.07 -0.12
98.105 0.501 99.095 -0.12
99.095 0.217 99.754 -0.02
99.759 0.046 99.759 -0.0238
100 0 100 0
X Y
1 0
0.99759 0.00046
0.99095 0.00217
0.98105 0.00501
0.96827 0.00843
0.95247 0.01204
0.93354 0.01594
0.91163 0.02027
0.88697 0.02505
0.85984 0.03027
0.83047 0.0359
0.79916 0.04189
0.76618 0.04816
0.73183 0.05463
0.69641 0.06119
0.66022 0.06771
0.62357 0.07402
0.58668 0.07986
0.54969 0.08509
0.51279 0.08963
0.47611 0.09328
0.43972 0.09598
0.40381 0.09776
0.36848 0.09853
0.3338 0.09838
0.29999 0.09735
0.26722 0.09547
0.23564 0.0928
0.20545 0.08939
0.17681 0.08528
0.14988 0.08053
0.12484 0.0752
0.10184 0.06934
0.08104 0.06296
0.06251 0.0561
0.04638 0.04885
0.03271 0.04115
0.02141 0.03305
0.01256 0.02483
0.00612 0.01649
0.00193 0.00823
1E-05 0.00054
1E-05 0.00054
0.00098 -0.00588
0.00548 -0.01153
0.01338 -0.0172
0.02433 -0.02273
0.03811 -0.02804
0.05468 -0.03304
0.07395 -0.03773
0.09576 -0.04208
0.11999 -0.04605
0.14648 -0.04964
0.17504 -0.05283
0.20549 -0.05558
0.2376 -0.05786
0.2712 -0.05962
0.30609 -0.06084
0.34204 -0.06146
0.37887 -0.06147
0.41638 -0.06087
0.45435 -0.05959
0.49265 -0.05765
0.53099 -0.05502
0.56937 -0.05165
0.60778 -0.04772
0.64594 -0.04348
0.68359 -0.03907
0.72043 -0.03464
0.75616 -0.03028
0.79048 -0.02609
0.82309 -0.02215
0.8537 -0.01852
0.88202 -0.01523
0.90775 -0.0123
0.93064 -0.0097
0.95044 -0.00739
0.96698 -0.00519
0.98037 -0.00302
0.9907 -0.0012
0.99095 -0.0012
0.99754 -0.0002
0.99759 -0.000238
1 0
X Y
100 0
99.759 0.046
99.095 0.217
98.105 0.501
96.827 0.843
95.247 1.204
93.354 1.594
91.163 2.027
88.697 2.505
85.984 3.027
83.047 3.59
79.916 4.189
76.618 4.816
73.183 5.463
69.641 6.119
66.022 6.771
62.357 7.402
58.668 7.986
54.969 8.509
51.279 8.963
47.611 9.328
43.972 9.598
40.381 9.776
36.848 9.853
33.38 9.838
29.999 9.735
26.722 9.547
23.564 9.28
20.545 8.939
17.681 8.528
14.988 8.053
12.484 7.52
10.184 6.934
8.104 6.296
6.251 5.61
4.638 4.885
3.271 4.115
2.141 3.305
1.256 2.483
0.612 1.649
0.193 0.823
0.001 0.054
0.001 0.054
0.098 -0.588
0.548 -1.153
1.338 -1.72
2.433 -2.273
3.811 -2.804
5.468 -3.304
7.395 -3.773
9.576 -4.208
11.999 -4.605
14.648 -4.964
17.504 -5.283
20.549 -5.558
23.76 -5.786
27.12 -5.962
30.609 -6.084
34.204 -6.146
37.887 -6.147
41.638 -6.087
45.435 -5.959
49.265 -5.765
53.099 -5.502
56.937 -5.165
60.778 -4.772
64.594 -4.348
68.359 -3.907
72.043 -3.464
75.616 -3.028
79.048 -2.609
82.309 -2.215
85.37 -1.852
88.202 -1.523
90.775 -1.23
93.064 -0.97
95.044 -0.739
96.698 -0.519
98.037 -0.302
99.07 -0.12
99.095 -0.12
99.754 -0.02
99.759 -0.0238
100 0
V 1.1