E212 (10.55%) (e212-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: E212 (10.55%) (e212-il) Reynolds number: 50,000 Max Cl/Cd: 38.27 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e212-il-50000.txt Download as CSV file: xf-e212-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: E212 (10.55%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4085 0.10798 0.10105 -0.0228 1.0000 0.2632
-8.250 -0.3836 0.10255 0.09559 -0.0213 1.0000 0.2710
-8.000 -0.4110 0.10250 0.09573 -0.0211 1.0000 0.2784
-7.750 -0.3909 0.09729 0.09051 -0.0201 1.0000 0.2823
-7.500 -0.3889 0.09428 0.08756 -0.0192 1.0000 0.2866
-7.250 -0.4213 0.09407 0.08758 -0.0175 1.0000 0.2941
-7.000 -0.4970 0.07136 0.06501 -0.0451 1.0000 0.1288
-6.750 -0.5093 0.06237 0.05583 -0.0516 1.0000 0.1177
-6.500 -0.5053 0.05649 0.04967 -0.0546 1.0000 0.1140
-6.250 -0.4957 0.05100 0.04386 -0.0573 1.0000 0.1131
-6.000 -0.4797 0.04555 0.03787 -0.0603 1.0000 0.1130
-5.750 -0.4574 0.04060 0.03225 -0.0630 1.0000 0.1140
-5.500 -0.4300 0.03630 0.02711 -0.0651 1.0000 0.1159
-5.250 -0.4070 0.03370 0.02449 -0.0650 1.0000 0.1225
-5.000 -0.3804 0.03123 0.02169 -0.0656 1.0000 0.1354
-4.750 -0.3529 0.02904 0.01925 -0.0658 1.0000 0.1574
-4.500 -0.3273 0.02749 0.01784 -0.0659 1.0000 0.2015
-4.250 -0.3029 0.02647 0.01708 -0.0655 1.0000 0.2617
-4.000 -0.2804 0.02574 0.01663 -0.0642 1.0000 0.3165
-3.750 -0.2573 0.02516 0.01613 -0.0632 1.0000 0.3708
-3.500 -0.2371 0.02482 0.01595 -0.0613 1.0000 0.4181
-3.250 -0.2172 0.02454 0.01574 -0.0594 1.0000 0.4638
-3.000 -0.1976 0.02432 0.01556 -0.0575 1.0000 0.5082
-2.750 -0.1812 0.02419 0.01556 -0.0547 1.0000 0.5468
-2.500 -0.1635 0.02404 0.01542 -0.0524 1.0000 0.5880
-2.250 -0.1486 0.02393 0.01535 -0.0494 1.0000 0.6258
-2.000 -0.1334 0.02382 0.01525 -0.0467 1.0000 0.6652
-1.750 -0.1208 0.02371 0.01518 -0.0434 1.0000 0.7031
-1.500 -0.1090 0.02358 0.01507 -0.0401 1.0000 0.7427
-1.250 -0.0991 0.02341 0.01491 -0.0365 1.0000 0.7850
-1.000 -0.0935 0.02314 0.01468 -0.0321 1.0000 0.8291
-0.750 -0.0911 0.02267 0.01430 -0.0271 1.0000 0.8826
-0.500 -0.0714 0.02174 0.01346 -0.0269 1.0000 0.9888
-0.250 -0.0231 0.02197 0.01332 -0.0353 1.0000 1.0000
0.000 0.0158 0.02247 0.01350 -0.0405 1.0000 1.0000
0.250 0.0471 0.02308 0.01385 -0.0437 1.0000 1.0000
0.500 0.0742 0.02375 0.01432 -0.0457 1.0000 1.0000
0.750 0.0987 0.02449 0.01488 -0.0472 1.0000 1.0000
1.000 0.1215 0.02529 0.01555 -0.0484 1.0000 1.0000
1.250 0.1430 0.02616 0.01631 -0.0494 1.0000 1.0000
1.500 0.1856 0.02753 0.01758 -0.0542 0.9888 1.0000
1.750 0.2398 0.02902 0.01897 -0.0608 0.9717 1.0000
2.000 0.2856 0.03010 0.02001 -0.0656 0.9532 1.0000
2.250 0.3353 0.03116 0.02105 -0.0708 0.9353 1.0000
2.500 0.3813 0.03206 0.02194 -0.0751 0.9172 1.0000
2.750 0.4216 0.03280 0.02273 -0.0782 0.8977 1.0000
3.000 0.4676 0.03344 0.02343 -0.0819 0.8788 1.0000
3.250 0.5171 0.03392 0.02399 -0.0858 0.8609 1.0000
3.500 0.5510 0.03443 0.02461 -0.0872 0.8397 1.0000
3.750 0.5951 0.03468 0.02498 -0.0897 0.8201 1.0000
4.000 0.6470 0.03451 0.02497 -0.0927 0.8018 1.0000
4.250 0.6819 0.03467 0.02531 -0.0934 0.7799 1.0000
4.500 0.7321 0.03403 0.02488 -0.0953 0.7601 1.0000
4.750 0.7974 0.03249 0.02364 -0.0984 0.7416 1.0000
5.000 0.8348 0.03204 0.02338 -0.0982 0.7171 1.0000
5.250 0.8947 0.03027 0.02188 -0.0998 0.6940 1.0000
5.500 0.9423 0.02906 0.02085 -0.0999 0.6659 1.0000
5.750 0.9803 0.02840 0.02030 -0.0991 0.6339 1.0000
6.000 1.0101 0.02821 0.02022 -0.0974 0.5986 1.0000
6.250 1.0440 0.02787 0.01984 -0.0960 0.5609 1.0000
6.500 1.0674 0.02815 0.02011 -0.0937 0.5208 1.0000
6.750 1.0912 0.02851 0.02039 -0.0914 0.4791 1.0000
7.000 1.1127 0.02910 0.02083 -0.0891 0.4358 1.0000
7.250 1.1317 0.02993 0.02146 -0.0865 0.3921 1.0000
7.500 1.1492 0.03099 0.02228 -0.0840 0.3488 1.0000
7.750 1.1631 0.03237 0.02356 -0.0813 0.3077 1.0000
8.000 1.1778 0.03398 0.02504 -0.0788 0.2691 1.0000
8.250 1.1930 0.03577 0.02661 -0.0764 0.2328 1.0000
8.500 1.2056 0.03781 0.02849 -0.0739 0.1989 1.0000
8.750 1.2134 0.03974 0.03035 -0.0710 0.1681 1.0000
9.000 1.2231 0.04202 0.03248 -0.0685 0.1415 1.0000
9.250 1.2361 0.04486 0.03540 -0.0664 0.1218 1.0000
9.500 1.2520 0.04828 0.03902 -0.0647 0.1094 1.0000
9.750 1.2658 0.05177 0.04273 -0.0631 0.1010 1.0000
10.000 1.2734 0.05526 0.04665 -0.0608 0.0956 1.0000
10.250 1.2912 0.05943 0.05088 -0.0601 0.0915 1.0000
10.500 1.2909 0.06400 0.05586 -0.0576 0.0903 1.0000
10.750 1.2816 0.06822 0.06058 -0.0545 0.0899 1.0000
11.000 1.2678 0.07248 0.06524 -0.0515 0.0897 1.0000
11.250 1.2499 0.07660 0.06966 -0.0484 0.0898 1.0000
11.500 1.2299 0.08096 0.07428 -0.0461 0.0900 1.0000
11.750 1.2093 0.08576 0.07929 -0.0447 0.0903 1.0000
12.000 1.1892 0.09109 0.08479 -0.0444 0.0907 1.0000
12.250 1.0787 0.10471 0.09889 -0.0538 0.0994 1.0000
12.500 1.0510 0.11461 0.10882 -0.0596 0.1019 1.0000
12.750 1.0359 0.12348 0.11769 -0.0642 0.1033 1.0000
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Polar data table (+)
Polar graphs
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