Airfoil:

mm

Job Status

Please wait while the PDF is generated...

Plot Number:

File:

Search for Airfoil
Winfoil Airfoils - Total Number: 277
Name T/C % T/C % Chord Position Camber % Camber Chord % CL Max CD Min
<< First < Prev 30 31 32 33 34 Next > Last >>
NACA 4403 3.03 34.5328 3.971 42.2134 0.896 0.0051
NACA 4412 12.02 30 3.943 40 1.649 0.0029
NACA 4415 14.99 30 3.939 40 1.588 0.0058
NACA 4418 18 30 3.934 40 1.551 0.0104
NACA 4508 8.11 27.03 3.925 48.44 0.94 0.0053
Coordinates
XUpper YUpper XLower YLower
0 0 0 0
0.5508 0.4536 0.6813 -0.2091
2.3296 1.1113 2.5686 -0.1616
5.2971 1.9249 5.6109 0.1079
9.3833 2.8214 9.7299 0.5446
14.489 3.711 14.8227 1.0773
20.4869 4.498 20.7652 1.6253
27.2255 5.0913 27.4149 2.1048
34.5328 5.4151 34.6136 2.4377
42.2134 5.423 42.1994 2.5662
50.0611 5.2109 50.0021 2.5655
57.903 4.8287 57.8091 2.4628
65.5447 4.2987 65.4291 2.2578
72.7977 3.6552 72.6746 1.9634
79.4837 2.942 79.3664 1.6039
85.4392 2.2101 85.3385 1.2118
90.5192 1.5133 90.4419 0.8238
94.6007 0.9047 94.5487 0.4766
97.585 0.4319 97.5557 0.2029
99.4007 0.1327 99.3869 0.0282
100.0041 0.0312 99.9958 -0.0312
X Y
1.000041 0.000312
0.994007 0.001327
0.97585 0.004319
0.946007 0.009047
0.905192 0.015133
0.854392 0.022101
0.794837 0.02942
0.727977 0.036552
0.655447 0.042987
0.57903 0.048287
0.500611 0.052109
0.422134 0.05423
0.345328 0.054151
0.272255 0.050913
0.204869 0.04498
0.14489 0.03711
0.093833 0.028214
0.052971 0.019249
0.023296 0.011113
0.005508 0.004536
0 0
0 0
0.006813 -0.002091
0.025686 -0.001616
0.056109 0.001079
0.097299 0.005446
0.148227 0.010773
0.207652 0.016253
0.274149 0.021048
0.346136 0.024377
0.421994 0.025662
0.500021 0.025655
0.578091 0.024628
0.654291 0.022578
0.726746 0.019634
0.793664 0.016039
0.853385 0.012118
0.904419 0.008238
0.945487 0.004766
0.975557 0.002029
0.993869 0.000282
0.999958 -0.000312
X Y
100.0041 0.0312
99.4007 0.1327
97.585 0.4319
94.6007 0.9047
90.5192 1.5133
85.4392 2.2101
79.4837 2.942
72.7977 3.6552
65.5447 4.2987
57.903 4.8287
50.0611 5.2109
42.2134 5.423
34.5328 5.4151
27.2255 5.0913
20.4869 4.498
14.489 3.711
9.3833 2.8214
5.2971 1.9249
2.3296 1.1113
0.5508 0.4536
0 0
0 0
0.6813 -0.2091
2.5686 -0.1616
5.6109 0.1079
9.7299 0.5446
14.8227 1.0773
20.7652 1.6253
27.4149 2.1048
34.6136 2.4377
42.1994 2.5662
50.0021 2.5655
57.8091 2.4628
65.4291 2.2578
72.6746 1.9634
79.3664 1.6039
85.3385 1.2118
90.4419 0.8238
94.5487 0.4766
97.5557 0.2029
99.3869 0.0282
99.9958 -0.0312
V 1.1