Eiffel 428 (Bleriot) (eiffel428-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: Eiffel 428 (Bleriot) (eiffel428-il) Reynolds number: 100,000 Max Cl/Cd: 50.49 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eiffel428-il-100000-n5.txt Download as CSV file: xf-eiffel428-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2561 0.08955 0.08509 -0.0381 1.0000 0.0571
-9.500 -0.2569 0.08654 0.08214 -0.0382 1.0000 0.0584
-9.250 -0.3358 0.09343 0.08871 -0.0374 1.0000 0.0547
-9.000 -0.3347 0.09083 0.08618 -0.0372 1.0000 0.0558
-8.750 -0.3371 0.08836 0.08380 -0.0369 1.0000 0.0567
-8.500 -0.3436 0.08617 0.08171 -0.0361 1.0000 0.0576
-8.250 -0.3533 0.08418 0.07985 -0.0349 1.0000 0.0585
-8.000 -0.2520 0.06466 0.06057 -0.0501 0.9600 0.0683
-7.750 -0.2347 0.06019 0.05607 -0.0545 0.9485 0.0721
-7.500 -0.2215 0.05397 0.04973 -0.0665 0.9335 0.0777
-7.000 -0.2468 0.05475 0.04989 -0.0755 0.9363 0.0535
-6.750 -0.2199 0.05142 0.04643 -0.0788 0.9248 0.0555
-6.500 -0.1894 0.04716 0.04192 -0.0836 0.9123 0.0578
-6.250 -0.1593 0.03950 0.03351 -0.0895 0.9012 0.0536
-6.000 -0.1306 0.03548 0.02891 -0.0918 0.8868 0.0532
-5.750 -0.1040 0.03380 0.02712 -0.0927 0.8696 0.0558
-5.500 -0.0785 0.03153 0.02444 -0.0931 0.8523 0.0575
-5.250 -0.0535 0.02908 0.02149 -0.0932 0.8372 0.0571
-5.000 -0.0282 0.02707 0.01902 -0.0929 0.8228 0.0570
-4.750 -0.0025 0.02542 0.01694 -0.0926 0.8095 0.0572
-4.500 0.0235 0.02403 0.01515 -0.0922 0.7971 0.0578
-4.250 0.0491 0.02293 0.01374 -0.0917 0.7853 0.0591
-4.000 0.0753 0.02208 0.01259 -0.0912 0.7743 0.0616
-3.750 0.1022 0.02123 0.01143 -0.0908 0.7638 0.0628
-3.500 0.1287 0.02038 0.01034 -0.0903 0.7520 0.0631
-3.250 0.1547 0.01965 0.00941 -0.0896 0.7390 0.0637
-3.000 0.1809 0.01902 0.00861 -0.0890 0.7271 0.0644
-2.750 0.2072 0.01834 0.00782 -0.0885 0.7176 0.0652
-2.500 0.2324 0.01764 0.00713 -0.0880 0.7082 0.0667
-2.250 0.2577 0.01714 0.00662 -0.0874 0.6991 0.0687
-2.000 0.2831 0.01677 0.00622 -0.0868 0.6901 0.0720
-1.750 0.3084 0.01649 0.00590 -0.0862 0.6809 0.0768
-1.500 0.3338 0.01620 0.00553 -0.0856 0.6721 0.0804
-1.250 0.3591 0.01591 0.00523 -0.0850 0.6618 0.0847
-1.000 0.3850 0.01572 0.00497 -0.0845 0.6522 0.0904
-0.750 0.4113 0.01550 0.00473 -0.0841 0.6425 0.1010
-0.500 0.4375 0.01483 0.00467 -0.0840 0.6297 0.2721
0.250 0.5446 0.01328 0.00450 -0.0887 0.5883 1.0000
0.500 0.5694 0.01340 0.00450 -0.0881 0.5771 1.0000
0.750 0.5943 0.01354 0.00453 -0.0874 0.5662 1.0000
1.000 0.6193 0.01368 0.00462 -0.0868 0.5565 1.0000
1.250 0.6442 0.01382 0.00471 -0.0862 0.5470 1.0000
1.500 0.6692 0.01398 0.00482 -0.0857 0.5378 1.0000
1.750 0.6935 0.01415 0.00493 -0.0849 0.5238 1.0000
2.000 0.7166 0.01436 0.00503 -0.0840 0.5007 1.0000
2.250 0.7382 0.01465 0.00512 -0.0828 0.4676 1.0000
2.500 0.7589 0.01503 0.00527 -0.0814 0.4309 1.0000
2.750 0.7792 0.01548 0.00552 -0.0801 0.3881 1.0000
3.000 0.7872 0.01693 0.00607 -0.0772 0.2411 1.0000
3.250 0.8062 0.01763 0.00659 -0.0759 0.2100 1.0000
3.500 0.8282 0.01805 0.00699 -0.0750 0.1916 1.0000
3.750 0.8476 0.01868 0.00751 -0.0738 0.1483 1.0000
4.000 0.8670 0.01930 0.00801 -0.0726 0.1384 1.0000
4.250 0.8855 0.01996 0.00859 -0.0713 0.1306 1.0000
4.500 0.9046 0.02055 0.00919 -0.0700 0.1241 1.0000
4.750 0.9220 0.02125 0.00993 -0.0685 0.1176 1.0000
5.000 0.9416 0.02175 0.01052 -0.0674 0.1133 1.0000
5.250 0.9612 0.02224 0.01112 -0.0662 0.1089 1.0000
5.500 0.9787 0.02288 0.01183 -0.0647 0.1049 1.0000
5.750 1.0002 0.02320 0.01235 -0.0637 0.0979 1.0000
6.000 1.0242 0.02334 0.01270 -0.0630 0.0675 1.0000
6.250 1.0356 0.02437 0.01347 -0.0608 0.0600 1.0000
6.500 1.0461 0.02542 0.01452 -0.0584 0.0567 1.0000
6.750 1.0545 0.02650 0.01568 -0.0557 0.0536 1.0000
7.000 1.0604 0.02768 0.01698 -0.0527 0.0506 1.0000
7.250 1.0641 0.02905 0.01844 -0.0496 0.0486 1.0000
7.500 1.0642 0.03077 0.02024 -0.0465 0.0468 1.0000
7.750 1.0732 0.03197 0.02160 -0.0444 0.0446 1.0000
8.000 1.0802 0.03344 0.02316 -0.0423 0.0419 1.0000
8.250 1.0870 0.03513 0.02488 -0.0403 0.0400 1.0000
8.500 1.0998 0.03720 0.02678 -0.0387 0.0380 1.0000
8.750 1.1142 0.03834 0.02812 -0.0374 0.0358 1.0000
9.000 1.1311 0.03973 0.02961 -0.0363 0.0332 1.0000
9.250 1.1545 0.04138 0.03133 -0.0357 0.0313 1.0000
9.500 1.1899 0.04376 0.03363 -0.0366 0.0290 1.0000
9.750 1.1971 0.04514 0.03535 -0.0346 0.0275 1.0000
10.000 1.2133 0.04708 0.03754 -0.0335 0.0260 1.0000
10.250 1.2298 0.04934 0.04004 -0.0326 0.0249 1.0000
10.500 1.2427 0.05170 0.04261 -0.0315 0.0240 1.0000
10.750 1.2527 0.05402 0.04509 -0.0304 0.0231 1.0000
11.000 1.2635 0.05670 0.04792 -0.0296 0.0222 1.0000
11.250 1.2634 0.05966 0.05112 -0.0280 0.0215 1.0000
11.500 1.2535 0.06235 0.05417 -0.0259 0.0210 1.0000
11.750 1.2454 0.06554 0.05769 -0.0244 0.0207 1.0000
12.000 1.2359 0.06909 0.06154 -0.0233 0.0205 1.0000
12.250 1.2239 0.07296 0.06570 -0.0226 0.0203 1.0000
12.500 1.2102 0.07716 0.07017 -0.0224 0.0202 1.0000
12.750 1.1945 0.08173 0.07501 -0.0227 0.0202 1.0000
13.000 1.1778 0.08668 0.08020 -0.0236 0.0201 1.0000
13.250 1.1600 0.09202 0.08576 -0.0251 0.0202 1.0000
13.500 1.1410 0.09785 0.09182 -0.0272 0.0202 1.0000
13.750 1.1215 0.10415 0.09832 -0.0300 0.0203 1.0000
14.000 1.1013 0.11110 0.10546 -0.0335 0.0203 1.0000
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Polar data table (+)
Polar graphs
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