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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 1 2 3 4 5 Next > Last >>
EPPLER 61 6.15 30 6.517 50 1.149 0.0005
NACA 64A410 9.96 38.26 2.115 51.68 1.065 0.0009
NACA 661-212 12 44.98 1.111 50 0.986 0.0011
NACA 65A-312 11.97 41.62 1.56 51.68 1.064 0.0012
EPPLER 378 4.08 10.36 8.109 35.92 1.686 0.0014
Coordinates
XUpper YUpper XLower YLower
0 0.95 0 1.32
0.12 1.94 0.12 0.59
0.55 2.28 0.55 0.25
0.99 2.46 0.99 0.19
1.25 2.7 1.25 0
2.5 3.4 2.5 0.15
5 4.7 5 0.5
7.5 5.8 7.5 0.95
10 6.5 10 1.1
15 7.6 15 2
20 8.4 20 2.3
30 9.3 30 3.15
40 9.95 40 4
50 9.8 50 4.2
60 8.8 60 4.3
70 7.7 70 4
80 6 80 3.1
90 3.7 90 2
95 2.15 95 1
100 0 100 0
X Y
1 0
0.95 0.0215
0.9 0.037
0.8 0.06
0.7 0.077
0.6 0.088
0.5 0.098
0.4 0.0995
0.3 0.093
0.2 0.084
0.15 0.076
0.1 0.065
0.075 0.058
0.05 0.047
0.025 0.034
0.0125 0.027
0.0099 0.0246
0.0055 0.0228
0.0012 0.0194
0 0.0095
0 0.0132
0.0012 0.0059
0.0055 0.0025
0.0099 0.0019
0.0125 0
0.025 0.0015
0.05 0.005
0.075 0.0095
0.1 0.011
0.15 0.02
0.2 0.023
0.3 0.0315
0.4 0.04
0.5 0.042
0.6 0.043
0.7 0.04
0.8 0.031
0.9 0.02
0.95 0.01
1 0
X Y
100 0
95 2.15
90 3.7
80 6
70 7.7
60 8.8
50 9.8
40 9.95
30 9.3
20 8.4
15 7.6
10 6.5
7.5 5.8
5 4.7
2.5 3.4
1.25 2.7
0.99 2.46
0.55 2.28
0.12 1.94
0 0.95
0 1.32
0.12 0.59
0.55 0.25
0.99 0.19
1.25 0
2.5 0.15
5 0.5
7.5 0.95
10 1.1
15 2
20 2.3
30 3.15
40 4
50 4.2
60 4.3
70 4
80 3.1
90 2
95 1
100 0
V 1.1