Eiffel 428 (Bleriot) (eiffel428-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: Eiffel 428 (Bleriot) (eiffel428-il) Reynolds number: 50,000 Max Cl/Cd: 38.57 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eiffel428-il-50000-n5.txt Download as CSV file: xf-eiffel428-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Eiffel 428 (Bleriot)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3350 0.09813 0.09156 -0.0338 1.0000 0.1315
-8.750 -0.3460 0.09675 0.09034 -0.0341 1.0000 0.1366
-8.500 -0.3702 0.09644 0.09027 -0.0363 1.0000 0.1385
-8.250 -0.3512 0.09158 0.08539 -0.0321 1.0000 0.1430
-8.000 -0.3544 0.08945 0.08338 -0.0312 1.0000 0.1481
-7.750 -0.3802 0.08932 0.08345 -0.0337 1.0000 0.1529
-7.500 -0.3769 0.08597 0.08019 -0.0294 1.0000 0.1560
-7.250 -0.3825 0.08436 0.07867 -0.0263 1.0000 0.1619
-7.000 -0.3847 0.08201 0.07638 -0.0284 0.9959 0.1708
-6.750 -0.3611 0.07809 0.07241 -0.0330 0.9856 0.1863
-6.500 -0.3132 0.06477 0.05831 -0.0572 0.9691 0.0932
-6.250 -0.2883 0.06067 0.05419 -0.0591 0.9612 0.0888
-6.000 -0.2596 0.05583 0.04907 -0.0644 0.9510 0.0860
-5.750 -0.2310 0.05172 0.04464 -0.0688 0.9411 0.0874
-5.500 -0.1959 0.04709 0.03956 -0.0738 0.9340 0.0850
-5.250 -0.1671 0.04298 0.03484 -0.0768 0.9239 0.0822
-5.000 -0.1305 0.03938 0.03052 -0.0802 0.9176 0.0805
-4.750 -0.1017 0.03700 0.02769 -0.0814 0.9085 0.0807
-4.500 -0.0651 0.03503 0.02551 -0.0840 0.9032 0.0847
-4.250 -0.0376 0.03339 0.02347 -0.0846 0.8936 0.0868
-4.000 0.0000 0.03147 0.02108 -0.0866 0.8880 0.0870
-3.750 0.0275 0.03016 0.01940 -0.0866 0.8783 0.0874
-3.500 0.0646 0.02878 0.01766 -0.0881 0.8720 0.0882
-3.250 0.0950 0.02774 0.01632 -0.0883 0.8612 0.0895
-3.000 0.1279 0.02678 0.01508 -0.0888 0.8505 0.0914
-2.750 0.1637 0.02576 0.01390 -0.0896 0.8400 0.0961
-2.500 0.1977 0.02492 0.01291 -0.0902 0.8285 0.1022
-2.250 0.2271 0.02431 0.01212 -0.0899 0.8160 0.1059
-2.000 0.2560 0.02378 0.01145 -0.0896 0.8045 0.1097
-1.750 0.2869 0.02319 0.01079 -0.0898 0.7953 0.1160
-1.500 0.3141 0.02278 0.01036 -0.0894 0.7841 0.1265
-1.250 0.3408 0.02226 0.01007 -0.0890 0.7722 0.1555
-1.000 0.3920 0.01938 0.00960 -0.0930 0.7607 1.0000
-0.750 0.4204 0.01941 0.00923 -0.0924 0.7502 1.0000
-0.500 0.4442 0.01959 0.00917 -0.0914 0.7384 1.0000
-0.250 0.4694 0.01980 0.00916 -0.0907 0.7295 1.0000
0.000 0.4958 0.01999 0.00917 -0.0903 0.7217 1.0000
0.250 0.5201 0.02026 0.00932 -0.0897 0.7133 1.0000
0.500 0.5463 0.02048 0.00942 -0.0893 0.7060 1.0000
0.750 0.5702 0.02078 0.00965 -0.0886 0.6979 1.0000
1.000 0.5959 0.02104 0.00983 -0.0882 0.6908 1.0000
1.250 0.6198 0.02136 0.01013 -0.0875 0.6829 1.0000
1.500 0.6450 0.02161 0.01035 -0.0870 0.6753 1.0000
1.750 0.6682 0.02195 0.01069 -0.0862 0.6667 1.0000
2.000 0.6938 0.02217 0.01092 -0.0857 0.6589 1.0000
2.250 0.7158 0.02255 0.01134 -0.0847 0.6498 1.0000
2.500 0.7419 0.02276 0.01155 -0.0843 0.6426 1.0000
2.750 0.7628 0.02321 0.01209 -0.0833 0.6336 1.0000
3.000 0.7891 0.02341 0.01236 -0.0828 0.6268 1.0000
3.250 0.8091 0.02383 0.01288 -0.0816 0.6161 1.0000
3.500 0.8307 0.02391 0.01301 -0.0801 0.6011 1.0000
3.750 0.8524 0.02384 0.01298 -0.0784 0.5826 1.0000
4.000 0.8727 0.02390 0.01308 -0.0767 0.5642 1.0000
4.250 0.8924 0.02414 0.01341 -0.0752 0.5476 1.0000
4.500 0.9114 0.02439 0.01375 -0.0735 0.5288 1.0000
4.750 0.9310 0.02462 0.01410 -0.0719 0.5097 1.0000
5.000 0.9509 0.02491 0.01448 -0.0705 0.4924 1.0000
5.250 0.9688 0.02524 0.01489 -0.0687 0.4690 1.0000
5.500 0.9871 0.02559 0.01528 -0.0669 0.4452 1.0000
5.750 1.0027 0.02606 0.01576 -0.0649 0.4112 1.0000
6.000 1.0161 0.02670 0.01638 -0.0626 0.3575 1.0000
6.250 1.0235 0.02767 0.01682 -0.0594 0.2743 1.0000
6.500 1.0247 0.02928 0.01800 -0.0561 0.2332 1.0000
6.750 1.0281 0.03077 0.01939 -0.0532 0.1995 1.0000
7.000 1.0269 0.03266 0.02105 -0.0503 0.1459 1.0000
7.250 1.0230 0.03490 0.02299 -0.0475 0.1313 1.0000
7.500 1.0212 0.03715 0.02517 -0.0452 0.1203 1.0000
7.750 1.0205 0.03945 0.02749 -0.0432 0.1088 1.0000
8.000 1.0249 0.04142 0.02970 -0.0417 0.0979 1.0000
8.250 1.0347 0.04300 0.03162 -0.0402 0.0833 1.0000
8.500 1.0425 0.04475 0.03346 -0.0392 0.0726 1.0000
8.750 1.0467 0.04688 0.03546 -0.0382 0.0674 1.0000
9.000 1.0491 0.04927 0.03776 -0.0373 0.0643 1.0000
9.250 1.0511 0.05175 0.04023 -0.0361 0.0622 1.0000
9.500 1.0552 0.05407 0.04264 -0.0349 0.0598 1.0000
9.750 1.0597 0.05640 0.04495 -0.0336 0.0569 1.0000
10.000 1.0732 0.05805 0.04670 -0.0316 0.0537 1.0000
10.250 1.1073 0.05854 0.04740 -0.0292 0.0507 1.0000
10.500 1.1654 0.05985 0.04881 -0.0279 0.0454 1.0000
10.750 1.1856 0.06255 0.05195 -0.0270 0.0438 1.0000
11.000 1.1989 0.06570 0.05549 -0.0260 0.0428 1.0000
11.250 1.2034 0.06912 0.05925 -0.0251 0.0416 1.0000
11.500 1.2045 0.07269 0.06310 -0.0242 0.0404 1.0000
12.000 1.2179 0.08141 0.07210 -0.0235 0.0378 1.0000
12.250 1.2019 0.08538 0.07637 -0.0231 0.0377 1.0000
12.500 1.1856 0.08974 0.08103 -0.0232 0.0376 1.0000
12.750 1.1691 0.09451 0.08606 -0.0239 0.0376 1.0000
13.000 1.1522 0.09963 0.09142 -0.0251 0.0376 1.0000
13.250 1.1355 0.10511 0.09711 -0.0269 0.0377 1.0000
13.500 1.1184 0.11097 0.10317 -0.0292 0.0378 1.0000
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Polar data table (+)
Polar graphs
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