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Winfoil Airfoils - Total Number: 277
Name T/C % Camber % Camber Chord % CL Max CD Min
<< First < Prev 7 8 9 10 11 Next > Last >>
ARA-D 10% 10.01 3.724 35 1.741 0.0202
ARA-D 13% 13 3.34 30 1.713 0.0247
ARA-D 6% 6.04 4.752 45 1.552 0.0145
ATR 14.52 2.882 21.4 1.632 0.0092
B-29 ROOT 21.92 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