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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 6 7 8 9 10 Next > Last >>
AH 79-100 B 10.04 30.87 6.542 53.27 1.451 0.0072
AH21 6.99 34.55 1.766 55.23 0.963 0.0044
AMSOIL 11.62 39 1.93 39 1.412 0.0122
AQUILA 9.39 31.33 4.045 34.67 1.426 0.0051
AQUILA 9.3% Smoothed 9.38 31.333 4.049 34.667 1.421 0.0046
Coordinates
XUpper YUpper XLower YLower
0.11 -0.32 0.11 0.54
0.43 1.06 0.43 -0.62
0.96 1.68 0.96 -0.87
1.7 2.34 1.7 -1.01
2.65 3.04 2.65 -1.07
3.81 3.74 3.81 -1.08
5.16 4.46 5.16 -1.05
6.7 5.2 6.7 -0.99
8.43 5.94 8.43 -0.9
10.33 6.65 10.33 -0.79
12.41 7.34 12.41 -0.66
14.65 7.97 14.65 -0.52
17.03 8.58 17.03 -0.37
19.56 9.12 19.56 -0.19
22.22 9.61 22.22 -0.01
25 10.03 25 0.18
27.89 10.38 27.89 0.39
30.87 10.65 30.87 0.61
33.93 10.85 33.93 0.84
37.06 10.96 37.06 1.09
40.25 11.01 40.25 1.35
43.47 10.98 43.47 1.62
46.73 10.87 46.73 1.88
53.27 10.44 53.27 2.39
56.53 10.1 56.53 2.61
59.76 9.7 59.76 2.79
62.94 9.23 62.94 2.93
66.07 8.72 66.07 3.03
69.13 8.15 69.13 3.09
72.11 7.56 72.11 3.11
75 6.95 75 3.09
77.78 6.34 77.78 3.03
80.44 5.73 80.44 2.93
82.97 5.13 82.97 2.79
85.36 4.54 85.36 2.61
87.59 3.98 87.59 2.4
89.67 3.43 89.67 2.16
91.57 2.92 91.57 1.91
93.3 2.42 93.3 1.63
94.84 1.96 94.84 1.35
96.19 1.52 96.19 1.07
97.35 1.12 97.35 0.79
98.3 0.76 98.3 0.52
99.04 0.44 99.04 0.31
99.57 0.19 99.57 0.13
99.89 0.03 99.89 0.01
X Y
0.9989 0.0003
0.9957 0.0019
0.9904 0.0044
0.983 0.0076
0.9735 0.0112
0.9619 0.0152
0.9484 0.0196
0.933 0.0242
0.9157 0.0292
0.8967 0.0343
0.8759 0.0398
0.8536 0.0454
0.8297 0.0513
0.8044 0.0573
0.7778 0.0634
0.75 0.0695
0.7211 0.0756
0.6913 0.0815
0.6607 0.0872
0.6294 0.0923
0.5976 0.097
0.5653 0.101
0.5327 0.1044
0.4673 0.1087
0.4347 0.1098
0.4025 0.1101
0.3706 0.1096
0.3393 0.1085
0.3087 0.1065
0.2789 0.1038
0.25 0.1003
0.2222 0.0961
0.1956 0.0912
0.1703 0.0858
0.1465 0.0797
0.1241 0.0734
0.1033 0.0665
0.0843 0.0594
0.067 0.052
0.0516 0.0446
0.0381 0.0374
0.0265 0.0304
0.017 0.0234
0.0096 0.0168
0.0043 0.0106
0.0011 -0.0032
0.0011 0.0054
0.0043 -0.0062
0.0096 -0.0087
0.017 -0.0101
0.0265 -0.0107
0.0381 -0.0108
0.0516 -0.0105
0.067 -0.0099
0.0843 -0.009
0.1033 -0.0079
0.1241 -0.0066
0.1465 -0.0052
0.1703 -0.0037
0.1956 -0.0019
0.2222 -0.0001
0.25 0.0018
0.2789 0.0039
0.3087 0.0061
0.3393 0.0084
0.3706 0.0109
0.4025 0.0135
0.4347 0.0162
0.4673 0.0188
0.5327 0.0239
0.5653 0.0261
0.5976 0.0279
0.6294 0.0293
0.6607 0.0303
0.6913 0.0309
0.7211 0.0311
0.75 0.0309
0.7778 0.0303
0.8044 0.0293
0.8297 0.0279
0.8536 0.0261
0.8759 0.024
0.8967 0.0216
0.9157 0.0191
0.933 0.0163
0.9484 0.0135
0.9619 0.0107
0.9735 0.0079
0.983 0.0052
0.9904 0.0031
0.9957 0.0013
0.9989 0.0001
X Y
99.89 0.03
99.57 0.19
99.04 0.44
98.3 0.76
97.35 1.12
96.19 1.52
94.84 1.96
93.3 2.42
91.57 2.92
89.67 3.43
87.59 3.98
85.36 4.54
82.97 5.13
80.44 5.73
77.78 6.34
75 6.95
72.11 7.56
69.13 8.15
66.07 8.72
62.94 9.23
59.76 9.7
56.53 10.1
53.27 10.44
46.73 10.87
43.47 10.98
40.25 11.01
37.06 10.96
33.93 10.85
30.87 10.65
27.89 10.38
25 10.03
22.22 9.61
19.56 9.12
17.03 8.58
14.65 7.97
12.41 7.34
10.33 6.65
8.43 5.94
6.7 5.2
5.16 4.46
3.81 3.74
2.65 3.04
1.7 2.34
0.96 1.68
0.43 1.06
0.11 -0.32
0.11 0.54
0.43 -0.62
0.96 -0.87
1.7 -1.01
2.65 -1.07
3.81 -1.08
5.16 -1.05
6.7 -0.99
8.43 -0.9
10.33 -0.79
12.41 -0.66
14.65 -0.52
17.03 -0.37
19.56 -0.19
22.22 -0.01
25 0.18
27.89 0.39
30.87 0.61
33.93 0.84
37.06 1.09
40.25 1.35
43.47 1.62
46.73 1.88
53.27 2.39
56.53 2.61
59.76 2.79
62.94 2.93
66.07 3.03
69.13 3.09
72.11 3.11
75 3.09
77.78 3.03
80.44 2.93
82.97 2.79
85.36 2.61
87.59 2.4
89.67 2.16
91.57 1.91
93.3 1.63
94.84 1.35
96.19 1.07
97.35 0.79
98.3 0.52
99.04 0.31
99.57 0.13
99.89 0.01
V 1.1