E212 (10.55%) (e212-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E212 (10.55%) (e212-il) Reynolds number: 50,000 Max Cl/Cd: 40.59 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e212-il-50000-n5.txt Download as CSV file: xf-e212-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3307 0.12167 0.11450 -0.0354 1.0000 0.0534
-11.250 -0.3323 0.11797 0.11084 -0.0362 1.0000 0.0522
-10.750 -0.4431 0.11545 0.10787 -0.0375 1.0000 0.0474
-10.500 -0.4411 0.11178 0.10424 -0.0380 1.0000 0.0470
-10.250 -0.4403 0.10801 0.10053 -0.0387 1.0000 0.0466
-10.000 -0.4410 0.10411 0.09667 -0.0395 1.0000 0.0463
-9.750 -0.4434 0.10000 0.09263 -0.0404 1.0000 0.0460
-9.500 -0.4473 0.09575 0.08846 -0.0415 1.0000 0.0457
-9.250 -0.4530 0.09133 0.08413 -0.0427 1.0000 0.0453
-9.000 -0.4611 0.08667 0.07958 -0.0440 1.0000 0.0449
-8.750 -0.4726 0.08163 0.07465 -0.0456 1.0000 0.0445
-8.500 -0.4890 0.07616 0.06932 -0.0473 1.0000 0.0440
-8.250 -0.5107 0.07041 0.06365 -0.0499 1.0000 0.0433
-8.000 -0.5304 0.06410 0.05733 -0.0542 1.0000 0.0427
-7.750 -0.5442 0.05850 0.05155 -0.0570 1.0000 0.0423
-7.500 -0.5498 0.05328 0.04604 -0.0591 1.0000 0.0423
-7.250 -0.5469 0.04863 0.04101 -0.0607 1.0000 0.0425
-7.000 -0.5372 0.04458 0.03650 -0.0619 1.0000 0.0435
-6.750 -0.5224 0.04100 0.03240 -0.0628 1.0000 0.0451
-6.500 -0.5037 0.03778 0.02854 -0.0634 1.0000 0.0471
-6.250 -0.4846 0.03545 0.02605 -0.0633 1.0000 0.0494
-6.000 -0.4639 0.03348 0.02386 -0.0630 1.0000 0.0516
-5.750 -0.4420 0.03158 0.02169 -0.0626 1.0000 0.0546
-5.500 -0.4193 0.02985 0.01961 -0.0620 1.0000 0.0588
-5.250 -0.3971 0.02848 0.01825 -0.0619 1.0000 0.0663
-5.000 -0.3734 0.02707 0.01674 -0.0619 1.0000 0.0779
-4.750 -0.3482 0.02568 0.01537 -0.0623 1.0000 0.1009
-4.500 -0.3223 0.02455 0.01445 -0.0633 1.0000 0.1478
-4.250 -0.2971 0.02368 0.01369 -0.0638 1.0000 0.1991
-4.000 -0.2718 0.02308 0.01316 -0.0641 1.0000 0.2455
-3.750 -0.2470 0.02267 0.01278 -0.0642 1.0000 0.2898
-3.500 -0.2227 0.02238 0.01253 -0.0640 1.0000 0.3307
-3.250 -0.1987 0.02218 0.01234 -0.0637 1.0000 0.3699
-3.000 -0.1754 0.02205 0.01220 -0.0632 1.0000 0.4076
-2.750 -0.1524 0.02197 0.01211 -0.0627 1.0000 0.4445
-2.500 -0.1303 0.02195 0.01211 -0.0619 1.0000 0.4790
-2.250 -0.1086 0.02197 0.01213 -0.0611 0.9999 0.5133
-2.000 -0.0722 0.02214 0.01228 -0.0630 0.9923 0.5542
-1.750 -0.0366 0.02233 0.01249 -0.0646 0.9847 0.5925
-1.500 -0.0029 0.02244 0.01256 -0.0659 0.9759 0.6305
-1.250 0.0289 0.02253 0.01268 -0.0666 0.9668 0.6659
-1.000 0.0608 0.02261 0.01278 -0.0673 0.9578 0.7025
-0.750 0.0927 0.02266 0.01283 -0.0678 0.9486 0.7403
-0.500 0.1190 0.02262 0.01283 -0.0673 0.9377 0.7773
-0.250 0.1450 0.02254 0.01279 -0.0666 0.9269 0.8181
0.000 0.1724 0.02239 0.01267 -0.0661 0.9168 0.8662
0.250 0.2093 0.02213 0.01243 -0.0676 0.9065 0.9403
0.500 0.2494 0.02207 0.01225 -0.0708 0.8941 1.0000
0.750 0.2879 0.02219 0.01224 -0.0734 0.8829 1.0000
1.000 0.3290 0.02228 0.01221 -0.0763 0.8731 1.0000
1.250 0.3682 0.02233 0.01219 -0.0787 0.8622 1.0000
1.750 0.4391 0.02243 0.01222 -0.0817 0.8375 1.0000
2.000 0.4767 0.02240 0.01219 -0.0834 0.8258 1.0000
2.250 0.5189 0.02227 0.01207 -0.0856 0.8154 1.0000
2.500 0.5538 0.02225 0.01208 -0.0867 0.8015 1.0000
2.750 0.5883 0.02221 0.01210 -0.0875 0.7870 1.0000
3.000 0.6229 0.02216 0.01209 -0.0883 0.7720 1.0000
3.250 0.6578 0.02209 0.01208 -0.0890 0.7564 1.0000
3.500 0.6927 0.02200 0.01207 -0.0897 0.7400 1.0000
3.750 0.7223 0.02208 0.01223 -0.0895 0.7204 1.0000
4.000 0.7541 0.02210 0.01232 -0.0896 0.7007 1.0000
4.250 0.7876 0.02207 0.01237 -0.0899 0.6806 1.0000
4.500 0.8161 0.02222 0.01259 -0.0895 0.6575 1.0000
4.750 0.8474 0.02229 0.01270 -0.0893 0.6342 1.0000
5.000 0.8736 0.02254 0.01303 -0.0886 0.6079 1.0000
5.250 0.9003 0.02280 0.01334 -0.0878 0.5809 1.0000
5.500 0.9260 0.02312 0.01368 -0.0869 0.5529 1.0000
5.750 0.9502 0.02351 0.01411 -0.0858 0.5234 1.0000
6.000 0.9730 0.02397 0.01458 -0.0845 0.4929 1.0000
6.250 0.9944 0.02451 0.01513 -0.0831 0.4612 1.0000
6.500 1.0145 0.02513 0.01574 -0.0816 0.4288 1.0000
6.750 1.0334 0.02583 0.01645 -0.0799 0.3960 1.0000
7.000 1.0512 0.02662 0.01720 -0.0782 0.3634 1.0000
7.250 1.0677 0.02750 0.01805 -0.0764 0.3311 1.0000
7.500 1.0830 0.02849 0.01900 -0.0745 0.2989 1.0000
7.750 1.0972 0.02959 0.02008 -0.0725 0.2673 1.0000
8.000 1.1102 0.03081 0.02128 -0.0706 0.2374 1.0000
8.250 1.1220 0.03215 0.02257 -0.0685 0.2097 1.0000
8.500 1.1323 0.03360 0.02398 -0.0664 0.1841 1.0000
8.750 1.1418 0.03516 0.02556 -0.0642 0.1603 1.0000
9.000 1.1485 0.03691 0.02721 -0.0618 0.1400 1.0000
9.250 1.1539 0.03874 0.02908 -0.0595 0.1182 1.0000
9.500 1.1551 0.04074 0.03097 -0.0572 0.1003 1.0000
9.750 1.1585 0.04288 0.03319 -0.0552 0.0836 1.0000
10.000 1.1610 0.04526 0.03559 -0.0533 0.0722 1.0000
10.250 1.1635 0.04776 0.03814 -0.0516 0.0638 1.0000
10.500 1.1693 0.05036 0.04094 -0.0500 0.0569 1.0000
10.750 1.1709 0.05301 0.04360 -0.0486 0.0525 1.0000
11.000 1.1780 0.05579 0.04668 -0.0474 0.0481 1.0000
11.250 1.1825 0.05865 0.04973 -0.0463 0.0451 1.0000
11.500 1.1868 0.06159 0.05276 -0.0454 0.0432 1.0000
11.750 1.1923 0.06488 0.05623 -0.0446 0.0417 1.0000
12.000 1.1933 0.06877 0.06054 -0.0440 0.0405 1.0000
12.250 1.1890 0.07308 0.06520 -0.0439 0.0396 1.0000
12.500 1.1806 0.07784 0.07029 -0.0443 0.0389 1.0000
12.750 1.1686 0.08317 0.07591 -0.0456 0.0384 1.0000
13.000 1.1534 0.08921 0.08224 -0.0477 0.0382 1.0000
13.250 1.1349 0.09616 0.08946 -0.0509 0.0382 1.0000
13.500 1.1133 0.10427 0.09781 -0.0554 0.0385 1.0000
13.750 1.0891 0.11369 0.10743 -0.0612 0.0390 1.0000
14.000 1.0639 0.12446 0.11838 -0.0682 0.0397 1.0000
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Polar data table (+)
Polar graphs
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