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Winfoil Airfoils - Total Number: 277
Name T/C % T/C % Chord Position Camber % Camber Chord % CL Max CD Min
1 2 3 4 5 Next > Last >>
B-29 ROOT 21.92 29.94 1.782 39.94 1.699 0.0333
ARA-D 13% 13 25 3.34 30 1.713 0.0247
EPPLER 340 13.69 30.36 2.617 22.2 1.184 0.0246
WB13535 13.54 25 3.747 50 0.84 0.0241
EPPLER 325 12.61 30.45 1.812 18.29 0.845 0.0209
Coordinates
XUpper YUpper XLower YLower
0 0 0 0
0.83 2.33 0.61 -2.09
1.32 2.98 0.62 -2.1
2.56 4.25 0.88 -2.47
5.04 6.03 1.38 -3.07
7.52 7.39 2.64 -4.16
10.01 8.5 5.15 -5.48
14.98 10.23 7.66 -6.37
19.97 11.49 10.16 -7.03
24.95 12.3 15.17 -8.01
29.94 12.72 20.17 -8.69
39.94 12.53 25.17 -9.1
49.94 11.3 30.16 -9.26
59.95 9.34 40.15 -9.05
69.96 6.95 50.13 -8.34
79.98 4.45 60.11 -7.28
89.99 2.07 70.09 -5.91
95 0.98 80.06 -4.28
100 0 90.03 -2.35
X Y
1 0
0.95 0.0098
0.8999 0.0207
0.7998 0.0445
0.6996 0.0695
0.5995 0.0934
0.4994 0.113
0.3994 0.1253
0.2994 0.1272
0.2495 0.123
0.1997 0.1149
0.1498 0.1023
0.1001 0.085
0.0752 0.0739
0.0504 0.0603
0.0256 0.0425
0.0132 0.0298
0.0083 0.0233
0 0
0 0
0.0061 -0.0209
0.0062 -0.021
0.0088 -0.0247
0.0138 -0.0307
0.0264 -0.0416
0.0515 -0.0548
0.0766 -0.0637
0.1016 -0.0703
0.1517 -0.0801
0.2017 -0.0869
0.2517 -0.091
0.3016 -0.0926
0.4015 -0.0905
0.5013 -0.0834
0.6011 -0.0728
0.7009 -0.0591
0.8006 -0.0428
0.9003 -0.0235
X Y
100 0
95 0.98
89.99 2.07
79.98 4.45
69.96 6.95
59.95 9.34
49.94 11.3
39.94 12.53
29.94 12.72
24.95 12.3
19.97 11.49
14.98 10.23
10.01 8.5
7.52 7.39
5.04 6.03
2.56 4.25
1.32 2.98
0.83 2.33
0 0
0 0
0.61 -2.09
0.62 -2.1
0.88 -2.47
1.38 -3.07
2.64 -4.16
5.15 -5.48
7.66 -6.37
10.16 -7.03
15.17 -8.01
20.17 -8.69
25.17 -9.1
30.16 -9.26
40.15 -9.05
50.13 -8.34
60.11 -7.28
70.09 -5.91
80.06 -4.28
90.03 -2.35
V 1.1