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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 10 11 12 13 14 Next > Last >>
RAF 30 12.56 30 0.105 0.17 1.065 0.0004
RAF 27 9.7 30 0 0 0.854 0.0057
RAF 26 6.58 29.9 2.13 49.9 1.016 0.0041
RAF 25 6.43 29.85 1.043 49.86 0.746 0.0043
RAF 19 10.52 15 10.065 40 2.23 0.0084
Coordinates
XUpper YUpper XLower YLower
0 0 0 0
0.17 0.63 0.17 -0.53
0.43 1.17 0.43 -1
0.83 1.57 0.83 -1.57
1.25 1.8 1.25 -1.8
2.5 2.48 2.5 -2.48
5 3.46 5 -3.46
10 4.68 10 -4.68
15 5.44 15 -5.44
20 5.94 20 -5.94
30 6.32 30 -6.32
40 6.2 40 -6.2
50 5.66 50 -5.66
60 4.78 60 -4.78
70 3.7 70 -3.7
80 2.5 80 -2.5
90 1.3 90 -1.3
95 0.7 95 -0.7
100 0 100 0
X Y
1 0
0.95 0.007
0.9 0.013
0.8 0.025
0.7 0.037
0.6 0.0478
0.5 0.0566
0.4 0.062
0.3 0.0632
0.2 0.0594
0.15 0.0544
0.1 0.0468
0.05 0.0346
0.025 0.0248
0.0125 0.018
0.0083 0.0157
0.0043 0.0117
0.0017 0.0063
0 0
0 0
0.0017 -0.0053
0.0043 -0.01
0.0083 -0.0157
0.0125 -0.018
0.025 -0.0248
0.05 -0.0346
0.1 -0.0468
0.15 -0.0544
0.2 -0.0594
0.3 -0.0632
0.4 -0.062
0.5 -0.0566
0.6 -0.0478
0.7 -0.037
0.8 -0.025
0.9 -0.013
0.95 -0.007
1 0
X Y
100 0
95 0.7
90 1.3
80 2.5
70 3.7
60 4.78
50 5.66
40 6.2
30 6.32
20 5.94
15 5.44
10 4.68
5 3.46
2.5 2.48
1.25 1.8
0.83 1.57
0.43 1.17
0.17 0.63
0 0
0 0
0.17 -0.53
0.43 -1
0.83 -1.57
1.25 -1.8
2.5 -2.48
5 -3.46
10 -4.68
15 -5.44
20 -5.94
30 -6.32
40 -6.2
50 -5.66
60 -4.78
70 -3.7
80 -2.5
90 -1.3
95 -0.7
100 0
V 1.1