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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 9 10 11 12 13 Next > Last >>
CLARK W 11.21 30 3.684 40 1.643 0.0075
CLARK Y 11.73 30.87 3.528 43.47 1.595 0.006
CLARK YH 11.9 30 2.45 30 1.392 0.0095
CLARK YS 11.7 30 2.353 30 1.274 0.0055
DAE51 9.38 30.94 3.465 46.07 1.186 0.0078
Coordinates
XUpper YUpper XLower YLower
0 0 0 0
1.25 2.19 1.25 -1.61
2.5 3.11 2.5 -2.05
5 4.44 5 -2.57
7.5 5.45 7.5 -2.82
10 6.24 10 -2.93
15 7.49 15 -2.94
20 8.3 20 -2.79
30 9.04 30 -2.17
40 9.05 40 -1.54
50 8.59 50 -1.28
60 7.67 60 -1.23
70 6.32 70 -1.2
80 4.58 80 -0.94
90 2.52 90 -0.54
95 1.35 95 -0.28
100 0.1 100 0
X Y
1 0.001
0.95 0.0135
0.9 0.0252
0.8 0.0458
0.7 0.0632
0.6 0.0767
0.5 0.0859
0.4 0.0905
0.3 0.0904
0.2 0.083
0.15 0.0749
0.1 0.0624
0.075 0.0545
0.05 0.0444
0.025 0.0311
0.0125 0.0219
0 0
0 0
0.0125 -0.0161
0.025 -0.0205
0.05 -0.0257
0.075 -0.0282
0.1 -0.0293
0.15 -0.0294
0.2 -0.0279
0.3 -0.0217
0.4 -0.0154
0.5 -0.0128
0.6 -0.0123
0.7 -0.012
0.8 -0.0094
0.9 -0.0054
0.95 -0.0028
1 0
X Y
100 0.1
95 1.35
90 2.52
80 4.58
70 6.32
60 7.67
50 8.59
40 9.05
30 9.04
20 8.3
15 7.49
10 6.24
7.5 5.45
5 4.44
2.5 3.11
1.25 2.19
0 0
0 0
1.25 -1.61
2.5 -2.05
5 -2.57
7.5 -2.82
10 -2.93
15 -2.94
20 -2.79
30 -2.17
40 -1.54
50 -1.28
60 -1.23
70 -1.2
80 -0.94
90 -0.54
95 -0.28
100 0
V 1.1