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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 14 15 16 17 18 Next > Last >>
NACA M20 8.26 30 5.939 30 1.436 0.0096
NACA M12 11.9 30 1.942 30 1.382 0.01
NACA 747A415 14.98 40.18 3.048 34.96 1.297 0.0076
NACA 747A315 14.97 40.2 2.531 35 1.2 0.0102
NACA 671-215 14.98 50 1.111 50 0.803 0.0001
Coordinates
XUpper YUpper XLower YLower
0 0 0 0
1.25 1.7 1.25 -0.97
2.5 2.6 2.5 -0.94
5 4.17 5 -0.57
7.5 5.37 7.5 -0.13
10 6.47 10 0.31
15 8.03 15 1.03
20 9.14 20 1.56
30 10.21 30 2.06
40 9.99 40 1.9
50 8.92 50 1.33
60 7.3 60 0.58
70 5.4 70 -0.12
80 3.5 80 -0.55
90 1.78 90 -0.56
95 1.06 95 -0.36
100 0.47 100 0
X Y
1 0.0047
0.95 0.0106
0.9 0.0178
0.8 0.035
0.7 0.054
0.6 0.073
0.5 0.0892
0.4 0.0999
0.3 0.1021
0.2 0.0914
0.15 0.0803
0.1 0.0647
0.075 0.0537
0.05 0.0417
0.025 0.026
0.0125 0.017
0 0
0 0
0.0125 -0.0097
0.025 -0.0094
0.05 -0.0057
0.075 -0.0013
0.1 0.0031
0.15 0.0103
0.2 0.0156
0.3 0.0206
0.4 0.019
0.5 0.0133
0.6 0.0058
0.7 -0.0012
0.8 -0.0055
0.9 -0.0056
0.95 -0.0036
1 0
X Y
100 0.47
95 1.06
90 1.78
80 3.5
70 5.4
60 7.3
50 8.92
40 9.99
30 10.21
20 9.14
15 8.03
10 6.47
7.5 5.37
5 4.17
2.5 2.6
1.25 1.7
0 0
0 0
1.25 -0.97
2.5 -0.94
5 -0.57
7.5 -0.13
10 0.31
15 1.03
20 1.56
30 2.06
40 1.9
50 1.33
60 0.58
70 -0.12
80 -0.55
90 -0.56
95 -0.36
100 0
V 1.1