E222 (10.17%) (e222-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E222 (10.17%) (e222-il) Reynolds number: 100,000 Max Cl/Cd: 55.76 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e222-il-100000-n5.txt Download as CSV file: xf-e222-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E222 (10.17%)
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4573 0.09403 0.08885 -0.0392 1.0000 0.0279
-9.750 -0.4596 0.09000 0.08487 -0.0402 1.0000 0.0276
-9.500 -0.4636 0.08571 0.08064 -0.0415 1.0000 0.0273
-9.250 -0.4703 0.08100 0.07600 -0.0431 1.0000 0.0271
-9.000 -0.4797 0.07591 0.07099 -0.0451 1.0000 0.0268
-8.750 -0.4940 0.06989 0.06505 -0.0478 1.0000 0.0264
-8.500 -0.5205 0.06337 0.05859 -0.0516 1.0000 0.0261
-8.250 -0.5393 0.05828 0.05341 -0.0537 1.0000 0.0258
-8.000 -0.5543 0.05352 0.04849 -0.0543 1.0000 0.0256
-7.750 -0.5628 0.04910 0.04381 -0.0543 1.0000 0.0254
-7.500 -0.5651 0.04487 0.03925 -0.0540 1.0000 0.0253
-7.250 -0.5616 0.04097 0.03494 -0.0535 1.0000 0.0252
-7.000 -0.5528 0.03745 0.03098 -0.0529 1.0000 0.0253
-6.750 -0.5399 0.03446 0.02754 -0.0522 1.0000 0.0257
-6.500 -0.5237 0.03206 0.02465 -0.0515 1.0000 0.0267
-6.250 -0.5052 0.03009 0.02220 -0.0508 1.0000 0.0277
-6.000 -0.4856 0.02817 0.01995 -0.0500 1.0000 0.0282
-5.750 -0.4654 0.02628 0.01784 -0.0493 1.0000 0.0287
-5.500 -0.4342 0.02457 0.01595 -0.0507 0.9969 0.0294
-5.250 -0.4008 0.02321 0.01445 -0.0523 0.9932 0.0304
-5.000 -0.3677 0.02206 0.01314 -0.0538 0.9887 0.0316
-4.750 -0.3330 0.02106 0.01200 -0.0555 0.9845 0.0335
-4.500 -0.2999 0.02021 0.01098 -0.0569 0.9795 0.0361
-4.250 -0.2659 0.01938 0.01010 -0.0587 0.9743 0.0417
-4.000 -0.2300 0.01860 0.00924 -0.0606 0.9698 0.0510
-3.750 -0.1983 0.01762 0.00840 -0.0618 0.9634 0.0844
-3.500 -0.1627 0.01680 0.00794 -0.0640 0.9587 0.1662
-3.250 -0.1320 0.01609 0.00772 -0.0653 0.9519 0.2713
-3.000 -0.0979 0.01555 0.00756 -0.0670 0.9463 0.3740
-2.750 -0.0660 0.01523 0.00740 -0.0679 0.9395 0.4365
-2.500 -0.0323 0.01496 0.00723 -0.0690 0.9330 0.4927
-2.250 0.0000 0.01474 0.00710 -0.0698 0.9263 0.5449
-2.000 0.0324 0.01453 0.00697 -0.0704 0.9192 0.5950
-1.750 0.0646 0.01434 0.00685 -0.0709 0.9125 0.6419
-1.500 0.0961 0.01418 0.00675 -0.0712 0.9050 0.6855
-1.250 0.1270 0.01403 0.00663 -0.0713 0.8974 0.7272
-1.000 0.1573 0.01387 0.00652 -0.0711 0.8897 0.7663
-0.750 0.1843 0.01375 0.00643 -0.0703 0.8802 0.8034
-0.500 0.2162 0.01357 0.00625 -0.0704 0.8732 0.8402
-0.250 0.2422 0.01344 0.00614 -0.0693 0.8623 0.8771
0.000 0.2749 0.01329 0.00597 -0.0697 0.8527 0.9161
0.250 0.3200 0.01309 0.00573 -0.0728 0.8449 0.9549
0.500 0.3631 0.01295 0.00554 -0.0759 0.8333 1.0000
0.750 0.3938 0.01292 0.00543 -0.0765 0.8207 1.0000
1.000 0.4247 0.01290 0.00534 -0.0770 0.8078 1.0000
1.250 0.4554 0.01289 0.00527 -0.0774 0.7941 1.0000
1.500 0.4856 0.01291 0.00522 -0.0778 0.7797 1.0000
1.750 0.5153 0.01294 0.00521 -0.0780 0.7645 1.0000
2.000 0.5445 0.01299 0.00521 -0.0781 0.7486 1.0000
2.250 0.5734 0.01306 0.00523 -0.0781 0.7320 1.0000
2.500 0.6021 0.01315 0.00529 -0.0780 0.7150 1.0000
2.750 0.6290 0.01327 0.00538 -0.0777 0.6961 1.0000
3.000 0.6559 0.01341 0.00549 -0.0773 0.6766 1.0000
3.250 0.6831 0.01357 0.00559 -0.0769 0.6572 1.0000
3.500 0.7088 0.01375 0.00578 -0.0763 0.6359 1.0000
3.750 0.7348 0.01396 0.00594 -0.0758 0.6145 1.0000
4.000 0.7599 0.01419 0.00615 -0.0751 0.5915 1.0000
4.250 0.7849 0.01444 0.00636 -0.0744 0.5679 1.0000
4.500 0.8092 0.01473 0.00664 -0.0736 0.5428 1.0000
4.750 0.8331 0.01504 0.00692 -0.0727 0.5164 1.0000
5.000 0.8565 0.01538 0.00722 -0.0718 0.4891 1.0000
5.250 0.8793 0.01577 0.00756 -0.0708 0.4607 1.0000
5.500 0.9016 0.01619 0.00796 -0.0698 0.4311 1.0000
5.750 0.9233 0.01666 0.00837 -0.0687 0.4005 1.0000
6.000 0.9444 0.01718 0.00883 -0.0675 0.3692 1.0000
6.250 0.9650 0.01774 0.00933 -0.0663 0.3370 1.0000
6.500 0.9850 0.01836 0.00988 -0.0650 0.3041 1.0000
6.750 1.0043 0.01904 0.01053 -0.0637 0.2715 1.0000
7.000 1.0229 0.01980 0.01120 -0.0624 0.2396 1.0000
7.250 1.0414 0.02060 0.01194 -0.0610 0.2092 1.0000
7.500 1.0592 0.02146 0.01274 -0.0597 0.1808 1.0000
7.750 1.0760 0.02241 0.01362 -0.0582 0.1522 1.0000
8.000 1.0916 0.02347 0.01454 -0.0567 0.1212 1.0000
8.250 1.1055 0.02470 0.01556 -0.0551 0.0894 1.0000
8.500 1.1196 0.02591 0.01665 -0.0535 0.0649 1.0000
8.750 1.1329 0.02719 0.01794 -0.0517 0.0482 1.0000
9.000 1.1429 0.02872 0.01949 -0.0494 0.0366 1.0000
9.250 1.1488 0.03039 0.02117 -0.0465 0.0306 1.0000
9.500 1.1564 0.03185 0.02279 -0.0440 0.0269 1.0000
9.750 1.1614 0.03352 0.02453 -0.0414 0.0241 1.0000
10.000 1.1667 0.03519 0.02635 -0.0390 0.0223 1.0000
10.250 1.1726 0.03687 0.02824 -0.0368 0.0206 1.0000
10.500 1.1768 0.03873 0.03026 -0.0347 0.0195 1.0000
10.750 1.1803 0.04072 0.03239 -0.0328 0.0188 1.0000
11.000 1.1824 0.04293 0.03473 -0.0311 0.0182 1.0000
11.250 1.1834 0.04539 0.03731 -0.0296 0.0177 1.0000
11.500 1.1850 0.04804 0.04010 -0.0282 0.0173 1.0000
11.750 1.1880 0.05072 0.04301 -0.0271 0.0169 1.0000
12.000 1.1899 0.05361 0.04613 -0.0262 0.0167 1.0000
12.250 1.1898 0.05682 0.04958 -0.0255 0.0164 1.0000
12.500 1.1878 0.06031 0.05333 -0.0251 0.0162 1.0000
12.750 1.1828 0.06425 0.05753 -0.0252 0.0160 1.0000
13.000 1.1755 0.06856 0.06210 -0.0257 0.0159 1.0000
13.250 1.1655 0.07340 0.06720 -0.0268 0.0158 1.0000
13.500 1.1534 0.07876 0.07281 -0.0287 0.0157 1.0000
13.750 1.1391 0.08475 0.07904 -0.0313 0.0157 1.0000
14.000 1.1229 0.09141 0.08594 -0.0347 0.0157 1.0000
14.250 1.1051 0.09890 0.09365 -0.0390 0.0158 1.0000
14.500 1.0857 0.10728 0.10225 -0.0441 0.0159 1.0000
14.750 1.0653 0.11662 0.11177 -0.0502 0.0161 1.0000
15.000 1.0434 0.12713 0.12244 -0.0570 0.0164 1.0000
15.250 1.0213 0.13858 0.13402 -0.0644 0.0166 1.0000
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Polar data table (+)
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