Eiffel 428 (Bleriot) (eiffel428-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: Eiffel 428 (Bleriot) (eiffel428-il) Reynolds number: 200,000 Max Cl/Cd: 67.72 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eiffel428-il-200000.txt Download as CSV file: xf-eiffel428-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3349 0.08844 0.08510 -0.0362 1.0000 0.0455
-8.750 -0.3360 0.08601 0.08274 -0.0359 1.0000 0.0464
-8.500 -0.3414 0.08383 0.08063 -0.0351 1.0000 0.0473
-8.250 -0.3538 0.08219 0.07910 -0.0331 1.0000 0.0479
-8.000 -0.3571 0.07967 0.07667 -0.0346 0.9970 0.0494
-7.750 -0.3043 0.07059 0.06729 -0.0644 0.9777 0.0532
-7.500 -0.2875 0.06399 0.06078 -0.0658 0.9710 0.0547
-7.250 -0.2615 0.06074 0.05751 -0.0675 0.9589 0.0564
-7.000 -0.2303 0.05662 0.05329 -0.0732 0.9471 0.0594
-6.750 -0.1873 0.04815 0.04416 -0.0886 0.9325 0.0671
-6.500 -0.1607 0.04522 0.04139 -0.0897 0.9222 0.0694
-6.250 -0.1296 0.04244 0.03850 -0.0928 0.9097 0.0733
-6.000 -0.1007 0.03762 0.03308 -0.0974 0.8940 0.0825
-5.750 -0.0770 0.03563 0.03110 -0.0978 0.8785 0.0853
-5.500 -0.0548 0.03326 0.02825 -0.0985 0.8627 0.0976
-5.250 -0.0337 0.03164 0.02667 -0.0980 0.8476 0.1016
-5.000 -0.0123 0.02970 0.02440 -0.0978 0.8348 0.1141
-4.750 0.0092 0.02838 0.02282 -0.0973 0.8220 0.1282
-4.500 0.0304 0.02724 0.02155 -0.0966 0.8083 0.1430
-4.250 0.0517 0.02615 0.02041 -0.0958 0.7944 0.1585
-3.750 0.1123 0.02011 0.01250 -0.0929 0.7751 0.0811
-3.500 0.1367 0.01804 0.01027 -0.0922 0.7635 0.0771
-3.250 0.1625 0.01694 0.00894 -0.0914 0.7528 0.0754
-3.000 0.1884 0.01626 0.00804 -0.0907 0.7417 0.0765
-2.750 0.2144 0.01557 0.00718 -0.0899 0.7308 0.0769
-2.500 0.2404 0.01490 0.00640 -0.0893 0.7200 0.0768
-2.250 0.2664 0.01435 0.00575 -0.0886 0.7102 0.0776
-2.000 0.2923 0.01389 0.00522 -0.0879 0.7006 0.0787
-1.750 0.3180 0.01352 0.00483 -0.0873 0.6914 0.0802
-1.500 0.3426 0.01293 0.00426 -0.0866 0.6828 0.0846
-1.250 0.3674 0.01260 0.00395 -0.0858 0.6714 0.0889
-1.000 0.3926 0.01236 0.00368 -0.0851 0.6605 0.0932
-0.750 0.4178 0.01212 0.00339 -0.0844 0.6502 0.1006
-0.500 0.4428 0.01185 0.00317 -0.0837 0.6389 0.1208
-0.250 0.5108 0.00954 0.00314 -0.0927 0.6242 1.0000
0.000 0.5359 0.00962 0.00309 -0.0920 0.6136 1.0000
0.250 0.5610 0.00971 0.00307 -0.0913 0.6046 1.0000
0.500 0.5860 0.00980 0.00307 -0.0907 0.5941 1.0000
0.750 0.6105 0.00990 0.00309 -0.0899 0.5800 1.0000
1.000 0.6346 0.01002 0.00309 -0.0890 0.5630 1.0000
1.250 0.6588 0.01015 0.00313 -0.0883 0.5463 1.0000
1.500 0.6823 0.01031 0.00317 -0.0873 0.5227 1.0000
1.750 0.7041 0.01056 0.00323 -0.0861 0.4891 1.0000
2.000 0.7270 0.01080 0.00334 -0.0851 0.4648 1.0000
2.250 0.7497 0.01107 0.00349 -0.0841 0.4408 1.0000
2.500 0.7716 0.01140 0.00366 -0.0830 0.4116 1.0000
2.750 0.7900 0.01198 0.00394 -0.0814 0.3438 1.0000
3.000 0.7995 0.01336 0.00460 -0.0786 0.2184 1.0000
3.250 0.8206 0.01383 0.00496 -0.0775 0.1888 1.0000
3.750 0.8584 0.01509 0.00586 -0.0748 0.1321 1.0000
4.000 0.8792 0.01554 0.00631 -0.0736 0.1247 1.0000
4.250 0.8981 0.01613 0.00690 -0.0722 0.1174 1.0000
4.500 0.9200 0.01648 0.00730 -0.0713 0.1124 1.0000
4.750 0.9409 0.01690 0.00778 -0.0702 0.1067 1.0000
5.000 0.9629 0.01723 0.00816 -0.0692 0.1000 1.0000
5.250 0.9866 0.01744 0.00843 -0.0684 0.0908 1.0000
5.500 1.0079 0.01782 0.00864 -0.0674 0.0626 1.0000
5.750 1.0225 0.01869 0.00951 -0.0653 0.0577 1.0000
6.000 1.0374 0.01949 0.01039 -0.0631 0.0550 1.0000
6.250 1.0502 0.02037 0.01138 -0.0608 0.0530 1.0000
6.500 1.0580 0.02152 0.01261 -0.0577 0.0504 1.0000
6.750 1.0618 0.02278 0.01389 -0.0541 0.0486 1.0000
7.000 1.0642 0.02430 0.01540 -0.0504 0.0472 1.0000
7.250 1.0736 0.02607 0.01713 -0.0479 0.0458 1.0000
7.500 1.0897 0.02695 0.01811 -0.0462 0.0444 1.0000
7.750 1.1079 0.02817 0.01938 -0.0449 0.0421 1.0000
8.000 1.1352 0.02973 0.02092 -0.0450 0.0405 1.0000
8.250 1.1812 0.03216 0.02327 -0.0481 0.0388 1.0000
8.500 1.2256 0.03616 0.02733 -0.0514 0.0362 1.0000
8.750 1.2422 0.03751 0.02895 -0.0496 0.0356 1.0000
9.000 1.2657 0.04003 0.03171 -0.0491 0.0356 1.0000
9.250 1.3052 0.04380 0.03555 -0.0508 0.0376 1.0000
9.500 1.2941 0.04366 0.03625 -0.0440 0.0413 1.0000
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Polar data table (+)
Polar graphs
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