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Winfoil Airfoils - Total Number: 277
Name T/C % Camber % Camber Chord % CL Max CD Min
<< First < Prev 51 52 53 54 55 Next > Last >>
P-51D ROOT (BL17.5) 16.45 1.266 68.267 1.482 0.0063
EPPLER 1200 16.93 3.48 40.77 1.818 0.0072
EPPLER 266 17.3 3.062 39.79 1.483 0.0066
NACA 65-218 17.95 1.123 50 1.399 0.0076
NACA 2418 17.96 1.95 40 1.367 0.0128
Coordinates
XUpper YUpper XLower YLower
0 0 0 0
0.558 1.52 0.558 -1.33
2.221 3.03 2.221 -2.64
4.952 4.47 4.952 -3.69
8.688 5.84 8.688 -4.67
13.347 6.97 13.347 -5.47
18.826 7.98 18.826 -6.14
25 8.73 25 -6.72
31.733 9.32 31.733 -7
38.874 9.47 38.874 -7.04
46.264 9 46.264 -6.73
53.736 8.14 53.736 -5.94
61.126 7.16 61.126 -4.79
68.267 6.15 68.267 -3.62
75 5.07 75 -2.65
81.175 3.81 81.175 -1.81
86.653 2.45 86.653 -1.05
91.312 1.37 91.312 -0.53
95.049 0.67 95.049 -0.25
97.779 0.28 97.779 -0.1
100 0 100 0
X Y
1 0
0.97779 0.0028
0.95049 0.0067
0.91312 0.0137
0.86653 0.0245
0.81175 0.0381
0.75 0.0507
0.68267 0.0615
0.61126 0.0716
0.53736 0.0814
0.46264 0.09
0.38874 0.0947
0.31733 0.0932
0.25 0.0873
0.18826 0.0798
0.13347 0.0697
0.08688 0.0584
0.04952 0.0447
0.02221 0.0303
0.00558 0.0152
0 0
0 0
0.00558 -0.0133
0.02221 -0.0264
0.04952 -0.0369
0.08688 -0.0467
0.13347 -0.0547
0.18826 -0.0614
0.25 -0.0672
0.31733 -0.07
0.38874 -0.0704
0.46264 -0.0673
0.53736 -0.0594
0.61126 -0.0479
0.68267 -0.0362
0.75 -0.0265
0.81175 -0.0181
0.86653 -0.0105
0.91312 -0.0053
0.95049 -0.0025
0.97779 -0.001
1 0
X Y
100 0
97.779 0.28
95.049 0.67
91.312 1.37
86.653 2.45
81.175 3.81
75 5.07
68.267 6.15
61.126 7.16
53.736 8.14
46.264 9
38.874 9.47
31.733 9.32
25 8.73
18.826 7.98
13.347 6.97
8.688 5.84
4.952 4.47
2.221 3.03
0.558 1.52
0 0
0 0
0.558 -1.33
2.221 -2.64
4.952 -3.69
8.688 -4.67
13.347 -5.47
18.826 -6.14
25 -6.72
31.733 -7
38.874 -7.04
46.264 -6.73
53.736 -5.94
61.126 -4.79
68.267 -3.62
75 -2.65
81.175 -1.81
86.653 -1.05
91.312 -0.53
95.049 -0.25
97.779 -0.1
100 0
V 1.1