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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 27 28 29 30 31 Next > Last >>
NACA 0010 9.97 30 0 0 0.877 0.0016
NACA 0009 8.97 30 0 0 0.871 0.0065
NACA 0008 7.98 30 0 0 0.765 0.0064
MILEY 12.86 35.03 5.132 35.03 1.43 0.005
MH62 9.29 27.91 1.409 37.15 0.919 0.0056
Coordinates
XUpper YUpper XLower YLower
0 0 0 0
0.25 0.7 0.25 -0.7
0.5 0.95 0.5 -0.95
1 1.4 1 -1.4
1.25 1.58 1.25 -1.58
2.5 2.18 2.5 -2.18
5 2.96 5 -2.96
7.5 3.5 7.5 -3.5
10 3.9 10 -3.9
15 4.46 15 -4.46
20 4.78 20 -4.78
25 4.95 25 -4.95
30 5 30 -5
40 4.84 40 -4.84
50 4.41 50 -4.41
60 3.8 60 -3.8
70 3.05 70 -3.05
80 2.19 80 -2.19
90 1.21 90 -1.21
100 0.11 100 -0.11
X Y
1 0.0011
0.9 0.0121
0.8 0.0219
0.7 0.0305
0.6 0.038
0.5 0.0441
0.4 0.0484
0.3 0.05
0.25 0.0495
0.2 0.0478
0.15 0.0446
0.1 0.039
0.075 0.035
0.05 0.0296
0.025 0.0218
0.0125 0.0158
0.01 0.014
0.005 0.0095
0.0025 0.007
0 0
0 0
0.0025 -0.007
0.005 -0.0095
0.01 -0.014
0.0125 -0.0158
0.025 -0.0218
0.05 -0.0296
0.075 -0.035
0.1 -0.039
0.15 -0.0446
0.2 -0.0478
0.25 -0.0495
0.3 -0.05
0.4 -0.0484
0.5 -0.0441
0.6 -0.038
0.7 -0.0305
0.8 -0.0219
0.9 -0.0121
1 -0.0011
X Y
100 0.11
90 1.21
80 2.19
70 3.05
60 3.8
50 4.41
40 4.84
30 5
25 4.95
20 4.78
15 4.46
10 3.9
7.5 3.5
5 2.96
2.5 2.18
1.25 1.58
1 1.4
0.5 0.95
0.25 0.7
0 0
0 0
0.25 -0.7
0.5 -0.95
1 -1.4
1.25 -1.58
2.5 -2.18
5 -2.96
7.5 -3.5
10 -3.9
15 -4.46
20 -4.78
25 -4.95
30 -5
40 -4.84
50 -4.41
60 -3.8
70 -3.05
80 -2.19
90 -1.21
100 -0.11
V 1.1