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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 52 53 54 55 56
ARA-D 13% 13 25 3.34 30 1.713 0.0247
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