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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 >>
ARA-D 13% 13 25 3.34 30 1.713 0.0247
SPICA 11.72 30 4.736 35 1.707 0.0071
GOTTINGEN 549 13.83 30 4.688 40 1.706 0.0084
GOTTINGE.COR 13.75 30 4.409 40 1.699 0.016
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 1.66 0.3 -0.88
1 3.05 1 -1.54
2 4.27 2 -2.05
4 5.88 4 -2.63
7 7.4 7 -3.03
10 8.38 10 -3.18
15 9.34 15 -3.17
20 9.83 20 -3.06
25 10.05 25 -2.94
30 10.07 30 -2.85
35 9.93 35 -2.76
40 9.64 40 -2.68
45 9.22 45 -2.58
50 8.7 50 -2.48
55 8.09 55 -2.36
60 7.42 60 -2.24
65 6.68 65 -2.12
70 5.9 70 -1.98
75 5.09 75 -1.83
80 4.26 80 -1.67
85 3.42 85 -1.49
90 2.58 90 -1.29
95 1.74 95 -1.07
97.5 1.32 97.5 -0.97
100 0.9 100 -0.9
X Y
1 0.009
0.975 0.0132
0.95 0.0174
0.9 0.0258
0.85 0.0342
0.8 0.0426
0.75 0.0509
0.7 0.059
0.65 0.0668
0.6 0.0742
0.55 0.0809
0.5 0.087
0.45 0.0922
0.4 0.0964
0.35 0.0993
0.3 0.1007
0.25 0.1005
0.2 0.0983
0.15 0.0934
0.1 0.0838
0.07 0.074
0.04 0.0588
0.02 0.0427
0.01 0.0305
0.003 0.0166
0 0
0 0
0.003 -0.0088
0.01 -0.0154
0.02 -0.0205
0.04 -0.0263
0.07 -0.0303
0.1 -0.0318
0.15 -0.0317
0.2 -0.0306
0.25 -0.0294
0.3 -0.0285
0.35 -0.0276
0.4 -0.0268
0.45 -0.0258
0.5 -0.0248
0.55 -0.0236
0.6 -0.0224
0.65 -0.0212
0.7 -0.0198
0.75 -0.0183
0.8 -0.0167
0.85 -0.0149
0.9 -0.0129
0.95 -0.0107
0.975 -0.0097
1 -0.009
X Y
100 0.9
97.5 1.32
95 1.74
90 2.58
85 3.42
80 4.26
75 5.09
70 5.9
65 6.68
60 7.42
55 8.09
50 8.7
45 9.22
40 9.64
35 9.93
30 10.07
25 10.05
20 9.83
15 9.34
10 8.38
7 7.4
4 5.88
2 4.27
1 3.05
0.3 1.66
0 0
0 0
0.3 -0.88
1 -1.54
2 -2.05
4 -2.63
7 -3.03
10 -3.18
15 -3.17
20 -3.06
25 -2.94
30 -2.85
35 -2.76
40 -2.68
45 -2.58
50 -2.48
55 -2.36
60 -2.24
65 -2.12
70 -1.98
75 -1.83
80 -1.67
85 -1.49
90 -1.29
95 -1.07
97.5 -0.97
100 -0.9
V 1.1