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Winfoil Airfoils - Total Number: 277
Name T/C % Camber % Camber Chord % CL Max CD Min
<< First < Prev 42 43 44 45 46 Next > Last >>
RAE(NPL) 5212 11.92 1.827 69.13 1.408 0.0053
RAF 15 6.45 2.564 30 1.282 0.0059
RAF 19 10.52 10.065 40 2.23 0.0084
RAF 25 6.43 1.043 49.86 0.746 0.0043
RAF 26 6.58 2.13 49.9 1.016 0.0041
Coordinates
XUpper YUpper XLower YLower
0 0 0 0
0.05 0.42 0.05 -0.34
0.1 0.6 0.1 -0.48
0.16 0.76 0.16 -0.59
0.24 0.94 0.24 -0.72
0.35 1.14 0.35 -0.85
0.5 1.37 0.5 -1
0.65 1.56 0.65 -1.12
0.8 1.74 0.8 -1.22
0.96 1.91 0.96 -1.32
1.5 2.4 1.5 -1.58
2.15 2.87 2.15 -1.83
3 3.34 3 -2.09
3.81 3.68 3.81 -2.29
5.9 4.32 5.9 -2.72
8.43 4.9 8.43 -3.13
11.35 5.42 11.35 -3.5
14.65 5.9 14.65 -3.84
18.28 6.3 18.28 -4.14
22.22 6.64 22.22 -4.38
26.43 6.91 26.43 -4.58
30.87 7.11 30.87 -4.69
35.49 7.23 35.49 -4.71
40.25 7.26 40.25 -4.61
45.1 7.2 45.1 -4.4
50 7.05 50 -4.05
54.9 6.79 54.9 -3.53
59.76 6.42 59.76 -2.95
64.51 5.94 64.51 -2.32
69.13 5.4 69.13 -1.73
73.57 4.81 73.57 -1.24
77.78 4.2 77.78 -0.84
81.72 3.57 81.72 -0.53
85.36 2.97 85.36 -0.31
88.65 2.4 88.65 -0.15
91.57 1.86 91.57 -0.05
94.1 1.33 94.1 0
96.19 0.86 96.19 0.01
97.85 0.46 97.85 0
99.04 0.19 99.04 0
99.76 0.04 99.76 0
100 0 100 0
X Y
1 0
0.9976 0.0004
0.9904 0.0019
0.9785 0.0046
0.9619 0.0086
0.941 0.0133
0.9157 0.0186
0.8865 0.024
0.8536 0.0297
0.8172 0.0357
0.7778 0.042
0.7357 0.0481
0.6913 0.054
0.6451 0.0594
0.5976 0.0642
0.549 0.0679
0.5 0.0705
0.451 0.072
0.4025 0.0726
0.3549 0.0723
0.3087 0.0711
0.2643 0.0691
0.2222 0.0664
0.1828 0.063
0.1465 0.059
0.1135 0.0542
0.0843 0.049
0.059 0.0432
0.0381 0.0368
0.03 0.0334
0.0215 0.0287
0.015 0.024
0.0096 0.0191
0.008 0.0174
0.0065 0.0156
0.005 0.0137
0.0035 0.0114
0.0024 0.0094
0.0016 0.0076
0.001 0.006
0.0005 0.0042
0 0
0 0
0.0005 -0.0034
0.001 -0.0048
0.0016 -0.0059
0.0024 -0.0072
0.0035 -0.0085
0.005 -0.01
0.0065 -0.0112
0.008 -0.0122
0.0096 -0.0132
0.015 -0.0158
0.0215 -0.0183
0.03 -0.0209
0.0381 -0.0229
0.059 -0.0272
0.0843 -0.0313
0.1135 -0.035
0.1465 -0.0384
0.1828 -0.0414
0.2222 -0.0438
0.2643 -0.0458
0.3087 -0.0469
0.3549 -0.0471
0.4025 -0.0461
0.451 -0.044
0.5 -0.0405
0.549 -0.0353
0.5976 -0.0295
0.6451 -0.0232
0.6913 -0.0173
0.7357 -0.0124
0.7778 -0.0084
0.8172 -0.0053
0.8536 -0.0031
0.8865 -0.0015
0.9157 -0.0005
0.941 0
0.9619 0.0001
0.9785 0
0.9904 0
0.9976 0
1 0
X Y
100 0
99.76 0.04
99.04 0.19
97.85 0.46
96.19 0.86
94.1 1.33
91.57 1.86
88.65 2.4
85.36 2.97
81.72 3.57
77.78 4.2
73.57 4.81
69.13 5.4
64.51 5.94
59.76 6.42
54.9 6.79
50 7.05
45.1 7.2
40.25 7.26
35.49 7.23
30.87 7.11
26.43 6.91
22.22 6.64
18.28 6.3
14.65 5.9
11.35 5.42
8.43 4.9
5.9 4.32
3.81 3.68
3 3.34
2.15 2.87
1.5 2.4
0.96 1.91
0.8 1.74
0.65 1.56
0.5 1.37
0.35 1.14
0.24 0.94
0.16 0.76
0.1 0.6
0.05 0.42
0 0
0 0
0.05 -0.34
0.1 -0.48
0.16 -0.59
0.24 -0.72
0.35 -0.85
0.5 -1
0.65 -1.12
0.8 -1.22
0.96 -1.32
1.5 -1.58
2.15 -1.83
3 -2.09
3.81 -2.29
5.9 -2.72
8.43 -3.13
11.35 -3.5
14.65 -3.84
18.28 -4.14
22.22 -4.38
26.43 -4.58
30.87 -4.69
35.49 -4.71
40.25 -4.61
45.1 -4.4
50 -4.05
54.9 -3.53
59.76 -2.95
64.51 -2.32
69.13 -1.73
73.57 -1.24
77.78 -0.84
81.72 -0.53
85.36 -0.31
88.65 -0.15
91.57 -0.05
94.1 0
96.19 0.01
97.85 0
99.04 0
99.76 0
100 0
V 1.1