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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 1 2 3 4 5 Next > Last >>
NACA 0015 15.01 28.73 0 0 1.287 0.0064
NACA 0016 15.91 27.3202 0 0 1.332 0.0106
NACA 0219 18.99 28.73 0 0 1.427 0.013
NACA 63-010 9.98 35 0 0 0.699 0.0065
RAF 27 9.7 30 0 0 0.854 0.0057
Coordinates
XUpper YUpper XLower YLower
0 0 0 0
0.1 0.69 0.1 -0.69
0.39 1.36 0.39 -1.36
0.89 2.01 0.89 -2.01
1.57 2.64 1.57 -2.64
3.51 3.81 3.51 -3.81
4.76 4.35 4.76 -4.35
6.19 4.86 6.19 -4.86
7.79 5.33 7.79 -5.33
11.48 6.15 11.48 -6.15
13.56 6.49 13.56 -6.49
15.78 6.79 15.78 -6.79
18.14 7.03 18.14 -7.03
23.23 7.37 23.23 -7.37
25.93 7.46 25.93 -7.46
28.73 7.51 28.73 -7.51
31.62 7.5 31.62 -7.5
37.59 7.36 37.59 -7.36
40.66 7.23 40.66 -7.23
43.76 7.06 43.76 -7.06
46.89 6.86 46.89 -6.86
53.17 6.36 53.17 -6.36
56.3 6.08 56.3 -6.08
59.4 5.78 59.4 -5.78
62.47 5.44 62.47 -5.44
68.44 4.77 68.44 -4.77
71.33 4.42 71.33 -4.42
74.12 4.06 74.12 -4.06
76.83 3.71 76.83 -3.71
81.91 3.01 81.91 -3.01
84.26 2.67 84.26 -2.67
86.48 2.35 86.48 -2.35
88.56 2.03 88.56 -2.03
92.24 1.46 92.24 -1.46
93.84 1.2 93.84 -1.2
95.26 0.96 95.26 -0.96
96.51 0.76 96.51 -0.76
98.44 0.43 98.44 -0.43
99.61 0.23 99.61 -0.23
100 0.16 100 -0.16
X Y
1 0.0016
0.9961 0.0023
0.9844 0.0043
0.9651 0.0076
0.9526 0.0096
0.9384 0.012
0.9224 0.0146
0.8856 0.0203
0.8648 0.0235
0.8426 0.0267
0.8191 0.0301
0.7683 0.0371
0.7412 0.0406
0.7133 0.0442
0.6844 0.0477
0.6247 0.0544
0.594 0.0578
0.563 0.0608
0.5317 0.0636
0.4689 0.0686
0.4376 0.0706
0.4066 0.0723
0.3759 0.0736
0.3162 0.075
0.2873 0.0751
0.2593 0.0746
0.2323 0.0737
0.1814 0.0703
0.1578 0.0679
0.1356 0.0649
0.1148 0.0615
0.0779 0.0533
0.0619 0.0486
0.0476 0.0435
0.0351 0.0381
0.0157 0.0264
0.0089 0.0201
0.0039 0.0136
0.001 0.0069
0 0
0 0
0.001 -0.0069
0.0039 -0.0136
0.0089 -0.0201
0.0157 -0.0264
0.0351 -0.0381
0.0476 -0.0435
0.0619 -0.0486
0.0779 -0.0533
0.1148 -0.0615
0.1356 -0.0649
0.1578 -0.0679
0.1814 -0.0703
0.2323 -0.0737
0.2593 -0.0746
0.2873 -0.0751
0.3162 -0.075
0.3759 -0.0736
0.4066 -0.0723
0.4376 -0.0706
0.4689 -0.0686
0.5317 -0.0636
0.563 -0.0608
0.594 -0.0578
0.6247 -0.0544
0.6844 -0.0477
0.7133 -0.0442
0.7412 -0.0406
0.7683 -0.0371
0.8191 -0.0301
0.8426 -0.0267
0.8648 -0.0235
0.8856 -0.0203
0.9224 -0.0146
0.9384 -0.012
0.9526 -0.0096
0.9651 -0.0076
0.9844 -0.0043
0.9961 -0.0023
1 -0.0016
X Y
100 0.16
99.61 0.23
98.44 0.43
96.51 0.76
95.26 0.96
93.84 1.2
92.24 1.46
88.56 2.03
86.48 2.35
84.26 2.67
81.91 3.01
76.83 3.71
74.12 4.06
71.33 4.42
68.44 4.77
62.47 5.44
59.4 5.78
56.3 6.08
53.17 6.36
46.89 6.86
43.76 7.06
40.66 7.23
37.59 7.36
31.62 7.5
28.73 7.51
25.93 7.46
23.23 7.37
18.14 7.03
15.78 6.79
13.56 6.49
11.48 6.15
7.79 5.33
6.19 4.86
4.76 4.35
3.51 3.81
1.57 2.64
0.89 2.01
0.39 1.36
0.1 0.69
0 0
0 0
0.1 -0.69
0.39 -1.36
0.89 -2.01
1.57 -2.64
3.51 -3.81
4.76 -4.35
6.19 -4.86
7.79 -5.33
11.48 -6.15
13.56 -6.49
15.78 -6.79
18.14 -7.03
23.23 -7.37
25.93 -7.46
28.73 -7.51
31.62 -7.5
37.59 -7.36
40.66 -7.23
43.76 -7.06
46.89 -6.86
53.17 -6.36
56.3 -6.08
59.4 -5.78
62.47 -5.44
68.44 -4.77
71.33 -4.42
74.12 -4.06
76.83 -3.71
81.91 -3.01
84.26 -2.67
86.48 -2.35
88.56 -2.03
92.24 -1.46
93.84 -1.2
95.26 -0.96
96.51 -0.76
98.44 -0.43
99.61 -0.23
100 -0.16
V 1.1