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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 20 21 22 23 24 Next > Last >>
NACA 6412 12.06 50 5.981 40 1.535 0.0075
NACA 6409 9.04 50 5.973 40 1.383 0
NACA 632-415 14.98 34.85 2.213 50 1.268 0.0028
NACA 632-215 14.97 34.93 1.114 50 0.998 0.0052
NACA 63-210 9.98 34.95 1.11 50 0.961 0.0061
Coordinates
XUpper YUpper XLower YLower
0 0 0 0
0.1 0.5 0.1 -0.2
0.2 0.8 0.2 -0.4
0.3 1 0.3 -0.45
0.4 1.2 0.4 -0.6
0.5 1.4 0.5 -0.7
1 2.05 1 -1
1.5 2.6 1.5 -1.3
2 3.15 2 -1.4
2.5 3.8 2.5 -1.64
5 5.36 5 -1.99
7.5 6.57 7.5 -2.05
10 7.58 10 -1.99
15 9.18 15 -1.67
20 10.34 20 -1.25
25 11.1 25 -0.82
30 11.65 30 -0.38
40 11.8 40 0.2
50 11.16 50 0.55
60 9.95 60 0.78
70 8.23 70 0.85
80 6.03 80 0.73
90 3.33 90 0.39
100 0 100 0
X Y
1 0
0.9 0.0333
0.8 0.0603
0.7 0.0823
0.6 0.0995
0.5 0.1116
0.4 0.118
0.3 0.1165
0.25 0.111
0.2 0.1034
0.15 0.0918
0.1 0.0758
0.075 0.0657
0.05 0.0536
0.025 0.038
0.02 0.0315
0.015 0.026
0.01 0.0205
0.005 0.014
0.004 0.012
0.003 0.01
0.002 0.008
0.001 0.005
0 0
0 0
0.001 -0.002
0.002 -0.004
0.003 -0.0045
0.004 -0.006
0.005 -0.007
0.01 -0.01
0.015 -0.013
0.02 -0.014
0.025 -0.0164
0.05 -0.0199
0.075 -0.0205
0.1 -0.0199
0.15 -0.0167
0.2 -0.0125
0.25 -0.0082
0.3 -0.0038
0.4 0.002
0.5 0.0055
0.6 0.0078
0.7 0.0085
0.8 0.0073
0.9 0.0039
1 0
X Y
100 0
90 3.33
80 6.03
70 8.23
60 9.95
50 11.16
40 11.8
30 11.65
25 11.1
20 10.34
15 9.18
10 7.58
7.5 6.57
5 5.36
2.5 3.8
2 3.15
1.5 2.6
1 2.05
0.5 1.4
0.4 1.2
0.3 1
0.2 0.8
0.1 0.5
0 0
0 0
0.1 -0.2
0.2 -0.4
0.3 -0.45
0.4 -0.6
0.5 -0.7
1 -1
1.5 -1.3
2 -1.4
2.5 -1.64
5 -1.99
7.5 -2.05
10 -1.99
15 -1.67
20 -1.25
25 -0.82
30 -0.38
40 0.2
50 0.55
60 0.78
70 0.85
80 0.73
90 0.39
100 0
V 1.1