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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 47 48 49 50 51 Next > Last >>
NACA 23015 14.97 30 1.831 15 1.48 0.0116
NACA 747A315 14.97 40.2 2.531 35 1.2 0.0102
NACA 632-215 14.97 34.93 1.114 50 0.998 0.0052
NACA 2415 14.97 30 1.954 40 1.328 0.0082
NACA 652-215 14.97 39.95 1.115 50 0.958 0.0054
Coordinates
XUpper YUpper XLower YLower
0 0 0 0
0.15 1.4 0.15 -0.3
0.3 1.8 0.3 -0.6
0.6 2.4 0.6 -0.9
1.25 3.34 1.25 -1.54
2.5 4.44 2.5 -2.25
5 5.89 5 -3.04
7.5 6.9 7.5 -3.61
10 7.64 10 -4.09
15 8.52 15 -4.84
20 8.92 20 -5.41
25 9.08 25 -5.78
30 9.05 30 -5.96
40 8.59 40 -5.92
50 7.74 50 -5.5
60 6.61 60 -4.81
70 5.25 70 -3.91
80 3.73 80 -2.83
90 2.04 90 -1.59
95 1.12 95 -0.9
100 0.16 100 -0.16
X Y
1 0.0016
0.95 0.0112
0.9 0.0204
0.8 0.0373
0.7 0.0525
0.6 0.0661
0.5 0.0774
0.4 0.0859
0.3 0.0905
0.25 0.0908
0.2 0.0892
0.15 0.0852
0.1 0.0764
0.075 0.069
0.05 0.0589
0.025 0.0444
0.0125 0.0334
0.006 0.024
0.003 0.018
0.0015 0.014
0 0
0 0
0.0015 -0.003
0.003 -0.006
0.006 -0.009
0.0125 -0.0154
0.025 -0.0225
0.05 -0.0304
0.075 -0.0361
0.1 -0.0409
0.15 -0.0484
0.2 -0.0541
0.25 -0.0578
0.3 -0.0596
0.4 -0.0592
0.5 -0.055
0.6 -0.0481
0.7 -0.0391
0.8 -0.0283
0.9 -0.0159
0.95 -0.009
1 -0.0016
X Y
100 0.16
95 1.12
90 2.04
80 3.73
70 5.25
60 6.61
50 7.74
40 8.59
30 9.05
25 9.08
20 8.92
15 8.52
10 7.64
7.5 6.9
5 5.89
2.5 4.44
1.25 3.34
0.6 2.4
0.3 1.8
0.15 1.4
0 0
0 0
0.15 -0.3
0.3 -0.6
0.6 -0.9
1.25 -1.54
2.5 -2.25
5 -3.04
7.5 -3.61
10 -4.09
15 -4.84
20 -5.41
25 -5.78
30 -5.96
40 -5.92
50 -5.5
60 -4.81
70 -3.91
80 -2.83
90 -1.59
95 -0.9
100 -0.16
V 1.1