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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 29 30 31 32 33 Next > Last >>
NACA 2408 8.01 29.9 1.97 40 0.866 0.0068
NACA 2410 10.01 29.88 1.963 40 1.045 0.0091
NACA 2412 11.98 30 1.96 40 1.178 0.0093
NACA 2415 14.97 30 1.954 40 1.328 0.0082
NACA 2418 17.96 30 1.95 40 1.367 0.0128
Coordinates
XUpper YUpper XLower YLower
0 0 0 0
0.2 0.5 0.2 -0.4
0.5 0.8 0.5 -0.7
1 1.2 1 -1
2.34 1.98 2.66 -1.49
4.79 2.83 5.21 -1.89
7.27 3.47 7.73 -2.11
9.77 3.99 10.23 -2.24
14.78 4.78 15.22 -2.34
19.81 5.32 20.19 -2.32
24.85 5.68 25.15 -2.24
29.9 5.88 30.1 -2.13
40 5.87 40 -1.87
50.04 5.47 49.96 -1.59
60.07 4.82 59.93 -1.26
70.08 3.94 69.92 -0.94
80.08 2.86 79.92 -0.64
90.05 1.58 89.95 -0.35
95.03 0.86 94.97 -0.22
100 0.08 100 -0.08
X Y
1 0.0008
0.9503 0.0086
0.9005 0.0158
0.8008 0.0286
0.7008 0.0394
0.6007 0.0482
0.5004 0.0547
0.4 0.0587
0.299 0.0588
0.2485 0.0568
0.1981 0.0532
0.1478 0.0478
0.0977 0.0399
0.0727 0.0347
0.0479 0.0283
0.0234 0.0198
0.01 0.012
0.005 0.008
0.002 0.005
0 0
0 0
0.002 -0.004
0.005 -0.007
0.01 -0.01
0.0266 -0.0149
0.0521 -0.0189
0.0773 -0.0211
0.1023 -0.0224
0.1522 -0.0234
0.2019 -0.0232
0.2515 -0.0224
0.301 -0.0213
0.4 -0.0187
0.4996 -0.0159
0.5993 -0.0126
0.6992 -0.0094
0.7992 -0.0064
0.8995 -0.0035
0.9497 -0.0022
1 -0.0008
X Y
100 0.08
95.03 0.86
90.05 1.58
80.08 2.86
70.08 3.94
60.07 4.82
50.04 5.47
40 5.87
29.9 5.88
24.85 5.68
19.81 5.32
14.78 4.78
9.77 3.99
7.27 3.47
4.79 2.83
2.34 1.98
1 1.2
0.5 0.8
0.2 0.5
0 0
0 0
0.2 -0.4
0.5 -0.7
1 -1
2.66 -1.49
5.21 -1.89
7.73 -2.11
10.23 -2.24
15.22 -2.34
20.19 -2.32
25.15 -2.24
30.1 -2.13
40 -1.87
49.96 -1.59
59.93 -1.26
69.92 -0.94
79.92 -0.64
89.95 -0.35
94.97 -0.22
100 -0.08
V 1.1