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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 7 8 9 10 11 Next > Last >>
ARA-D 10% 10.01 25 3.724 35 1.741 0.0202
ARA-D 13% 13 25 3.34 30 1.713 0.0247
ARA-D 6% 6.04 20 4.752 45 1.552 0.0145
ATR 14.52 25.4 2.882 21.4 1.632 0.0092
B-29 ROOT 21.92 29.94 1.782 39.94 1.699 0.0333
Coordinates
XUpper YUpper XLower YLower
0 0 0 0
0.3 1.37 0.3 -0.73
1 2.52 1 -1.25
2 3.55 2 -1.63
4 4.92 4 -2
7 6.23 7 -2.16
10 7.08 10 -2.1
15 7.95 15 -1.82
20 8.46 20 -1.51
25 8.75 25 -1.25
30 8.89 30 -1.05
35 8.89 35 -0.91
40 8.76 40 -0.81
45 8.52 45 -0.73
50 8.17 50 -0.67
55 7.72 55 -0.63
60 7.2 60 -0.62
65 6.6 65 -0.62
70 5.93 70 -0.64
75 5.21 75 -0.66
80 4.42 80 -0.69
85 3.57 85 -0.71
90 2.66 90 -0.72
95 1.71 95 -0.72
97.5 1.23 97.5 -0.73
100 0.75 100 -0.75
X Y
1 0.0075
0.975 0.0123
0.95 0.0171
0.9 0.0266
0.85 0.0357
0.8 0.0442
0.75 0.0521
0.7 0.0593
0.65 0.066
0.6 0.072
0.55 0.0772
0.5 0.0817
0.45 0.0852
0.4 0.0876
0.35 0.0889
0.3 0.0889
0.25 0.0875
0.2 0.0846
0.15 0.0795
0.1 0.0708
0.07 0.0623
0.04 0.0492
0.02 0.0355
0.01 0.0252
0.003 0.0137
0 0
0 0
0.003 -0.0073
0.01 -0.0125
0.02 -0.0163
0.04 -0.02
0.07 -0.0216
0.1 -0.021
0.15 -0.0182
0.2 -0.0151
0.25 -0.0125
0.3 -0.0105
0.35 -0.0091
0.4 -0.0081
0.45 -0.0073
0.5 -0.0067
0.55 -0.0063
0.6 -0.0062
0.65 -0.0062
0.7 -0.0064
0.75 -0.0066
0.8 -0.0069
0.85 -0.0071
0.9 -0.0072
0.95 -0.0072
0.975 -0.0073
1 -0.0075
X Y
100 0.75
97.5 1.23
95 1.71
90 2.66
85 3.57
80 4.42
75 5.21
70 5.93
65 6.6
60 7.2
55 7.72
50 8.17
45 8.52
40 8.76
35 8.89
30 8.89
25 8.75
20 8.46
15 7.95
10 7.08
7 6.23
4 4.92
2 3.55
1 2.52
0.3 1.37
0 0
0 0
0.3 -0.73
1 -1.25
2 -1.63
4 -2
7 -2.16
10 -2.1
15 -1.82
20 -1.51
25 -1.25
30 -1.05
35 -0.91
40 -0.81
45 -0.73
50 -0.67
55 -0.63
60 -0.62
65 -0.62
70 -0.64
75 -0.66
80 -0.69
85 -0.71
90 -0.72
95 -0.72
97.5 -0.73
100 -0.75
V 1.1