E203 (13.64%) (e203-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E203 (13.64%) (e203-il) Reynolds number: 200,000 Max Cl/Cd: 78.18 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e203-il-200000.txt Download as CSV file: xf-e203-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: E203 (13.64%)
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4045 0.07451 0.07124 -0.0587 1.0000 0.0473
-10.750 -0.3875 0.07594 0.07268 -0.0558 1.0000 0.0483
-10.500 -0.5304 0.06794 0.06438 -0.0671 1.0000 0.0442
-10.250 -0.5568 0.06228 0.05868 -0.0701 1.0000 0.0434
-10.000 -0.5867 0.05802 0.05437 -0.0711 1.0000 0.0429
-9.750 -0.6176 0.05557 0.05189 -0.0684 1.0000 0.0425
-9.500 -0.6928 0.04847 0.04425 -0.0628 1.0000 0.0381
-9.250 -0.7010 0.04681 0.04225 -0.0590 1.0000 0.0361
-9.000 -0.7110 0.04322 0.03852 -0.0559 1.0000 0.0355
-8.750 -0.7190 0.04044 0.03551 -0.0527 1.0000 0.0352
-8.500 -0.6944 0.03576 0.03033 -0.0558 0.9948 0.0347
-8.250 -0.6643 0.03218 0.02624 -0.0586 0.9887 0.0349
-8.000 -0.6274 0.03005 0.02364 -0.0617 0.9838 0.0361
-7.750 -0.5943 0.02796 0.02121 -0.0637 0.9768 0.0365
-7.500 -0.5596 0.02485 0.01784 -0.0659 0.9725 0.0373
-7.250 -0.5266 0.02292 0.01584 -0.0676 0.9660 0.0387
-7.000 -0.4897 0.02155 0.01442 -0.0698 0.9602 0.0405
-6.750 -0.4522 0.02050 0.01329 -0.0721 0.9544 0.0437
-6.500 -0.4176 0.01932 0.01200 -0.0737 0.9469 0.0465
-6.250 -0.3786 0.01783 0.01056 -0.0766 0.9431 0.0516
-6.000 -0.3481 0.01672 0.00941 -0.0775 0.9333 0.0597
-5.750 -0.3110 0.01515 0.00808 -0.0800 0.9287 0.1003
-5.500 -0.2826 0.01407 0.00728 -0.0808 0.9181 0.1654
-5.250 -0.2494 0.01320 0.00667 -0.0824 0.9103 0.2310
-5.000 -0.2177 0.01244 0.00623 -0.0835 0.9013 0.3100
-4.750 -0.1878 0.01211 0.00609 -0.0840 0.8907 0.3832
-4.500 -0.1550 0.01202 0.00599 -0.0847 0.8815 0.4290
-4.250 -0.1245 0.01198 0.00586 -0.0850 0.8707 0.4565
-4.000 -0.0960 0.01198 0.00576 -0.0849 0.8591 0.4779
-3.750 -0.0673 0.01200 0.00567 -0.0848 0.8484 0.4979
-3.500 -0.0380 0.01199 0.00558 -0.0848 0.8388 0.5151
-3.250 -0.0115 0.01201 0.00552 -0.0844 0.8274 0.5299
-3.000 0.0159 0.01203 0.00544 -0.0841 0.8174 0.5438
-2.750 0.0442 0.01201 0.00537 -0.0840 0.8087 0.5564
-2.500 0.0704 0.01201 0.00533 -0.0835 0.7985 0.5680
-2.250 0.0980 0.01201 0.00526 -0.0834 0.7902 0.5797
-2.000 0.1253 0.01202 0.00519 -0.0832 0.7813 0.5915
-1.750 0.1523 0.01203 0.00517 -0.0829 0.7731 0.6024
-1.500 0.1797 0.01202 0.00512 -0.0827 0.7653 0.6128
-1.250 0.2067 0.01203 0.00510 -0.0825 0.7575 0.6237
-1.000 0.2343 0.01204 0.00506 -0.0824 0.7501 0.6348
-0.750 0.2611 0.01204 0.00508 -0.0821 0.7428 0.6452
-0.500 0.2884 0.01205 0.00507 -0.0820 0.7357 0.6565
-0.250 0.3156 0.01208 0.00508 -0.0818 0.7290 0.6686
0.000 0.3425 0.01209 0.00511 -0.0816 0.7218 0.6807
0.250 0.3701 0.01211 0.00513 -0.0815 0.7160 0.6930
0.500 0.3960 0.01212 0.00521 -0.0811 0.7086 0.7064
0.750 0.4237 0.01213 0.00523 -0.0810 0.7030 0.7213
1.000 0.4492 0.01216 0.00536 -0.0805 0.6961 0.7380
1.250 0.4758 0.01218 0.00542 -0.0802 0.6899 0.7572
1.500 0.5015 0.01221 0.00553 -0.0796 0.6841 0.7784
1.750 0.5257 0.01222 0.00566 -0.0788 0.6775 0.8044
2.000 0.5510 0.01223 0.00573 -0.0779 0.6723 0.8343
2.250 0.5728 0.01224 0.00592 -0.0764 0.6656 0.8711
2.500 0.6014 0.01223 0.00599 -0.0761 0.6596 0.9159
2.750 0.6442 0.01230 0.00610 -0.0791 0.6534 0.9603
3.000 0.6948 0.01235 0.00619 -0.0841 0.6460 0.9978
3.250 0.7206 0.01251 0.00626 -0.0841 0.6401 1.0000
3.500 0.7431 0.01267 0.00644 -0.0833 0.6321 1.0000
3.750 0.7705 0.01281 0.00651 -0.0832 0.6258 1.0000
4.000 0.7935 0.01295 0.00672 -0.0824 0.6171 1.0000
4.250 0.8212 0.01308 0.00678 -0.0823 0.6105 1.0000
4.500 0.8446 0.01321 0.00700 -0.0815 0.6014 1.0000
4.750 0.8710 0.01333 0.00709 -0.0812 0.5934 1.0000
5.000 0.8959 0.01341 0.00721 -0.0806 0.5840 1.0000
5.250 0.9204 0.01352 0.00738 -0.0799 0.5745 1.0000
5.500 0.9473 0.01359 0.00741 -0.0796 0.5657 1.0000
5.750 0.9703 0.01367 0.00758 -0.0786 0.5543 1.0000
6.000 0.9941 0.01374 0.00771 -0.0778 0.5428 1.0000
6.250 1.0179 0.01381 0.00783 -0.0769 0.5306 1.0000
6.500 1.0412 0.01387 0.00793 -0.0759 0.5173 1.0000
6.750 1.0634 0.01395 0.00806 -0.0748 0.5022 1.0000
7.000 1.0848 0.01405 0.00822 -0.0735 0.4850 1.0000
7.250 1.1055 0.01419 0.00840 -0.0721 0.4654 1.0000
7.500 1.1250 0.01439 0.00862 -0.0705 0.4430 1.0000
7.750 1.1426 0.01467 0.00888 -0.0686 0.4154 1.0000
8.000 1.1569 0.01511 0.00923 -0.0662 0.3774 1.0000
8.250 1.1653 0.01584 0.00973 -0.0630 0.3268 1.0000
8.500 1.1669 0.01694 0.01049 -0.0589 0.2703 1.0000
8.750 1.1660 0.01813 0.01139 -0.0546 0.2221 1.0000
9.000 1.1644 0.01937 0.01238 -0.0503 0.1834 1.0000
9.250 1.1656 0.02061 0.01344 -0.0467 0.1516 1.0000
9.500 1.1669 0.02193 0.01461 -0.0434 0.1259 1.0000
9.750 1.1691 0.02329 0.01587 -0.0404 0.1044 1.0000
10.000 1.1700 0.02483 0.01731 -0.0376 0.0872 1.0000
10.250 1.1713 0.02646 0.01891 -0.0351 0.0716 1.0000
10.500 1.1696 0.02844 0.02083 -0.0326 0.0573 1.0000
10.750 1.1660 0.03071 0.02308 -0.0303 0.0461 1.0000
11.000 1.1626 0.03312 0.02550 -0.0283 0.0390 1.0000
11.250 1.1601 0.03558 0.02795 -0.0268 0.0344 1.0000
11.500 1.1612 0.03786 0.03032 -0.0254 0.0316 1.0000
11.750 1.1641 0.04004 0.03257 -0.0243 0.0293 1.0000
12.000 1.1661 0.04236 0.03492 -0.0233 0.0278 1.0000
12.250 1.1659 0.04504 0.03758 -0.0219 0.0264 1.0000
12.500 1.1744 0.04694 0.03961 -0.0210 0.0255 1.0000
12.750 1.1833 0.04887 0.04166 -0.0200 0.0245 1.0000
13.000 1.1918 0.05089 0.04378 -0.0192 0.0234 1.0000
13.250 1.2003 0.05293 0.04592 -0.0186 0.0226 1.0000
13.500 1.2081 0.05504 0.04808 -0.0181 0.0218 1.0000
13.750 1.2212 0.05723 0.05027 -0.0171 0.0207 1.0000
14.000 1.2260 0.05999 0.05324 -0.0166 0.0201 1.0000
14.250 1.2324 0.06272 0.05616 -0.0161 0.0200 1.0000
14.500 1.2333 0.06590 0.05957 -0.0159 0.0197 1.0000
14.750 1.2318 0.06952 0.06343 -0.0159 0.0195 1.0000
15.000 1.2278 0.07344 0.06758 -0.0162 0.0194 1.0000
15.250 1.2204 0.07791 0.07231 -0.0169 0.0194 1.0000
15.500 1.2106 0.08273 0.07737 -0.0180 0.0194 1.0000
15.750 1.1988 0.08801 0.08288 -0.0195 0.0195 1.0000
16.000 1.1833 0.09398 0.08910 -0.0217 0.0194 1.0000
16.250 1.1673 0.10031 0.09565 -0.0244 0.0195 1.0000
16.500 1.1496 0.10721 0.10277 -0.0277 0.0196 1.0000
16.750 1.1317 0.11451 0.11028 -0.0316 0.0198 1.0000
17.000 1.1126 0.12238 0.11833 -0.0361 0.0199 1.0000
17.250 1.0943 0.13056 0.12668 -0.0410 0.0201 1.0000
17.500 1.0735 0.13978 0.13605 -0.0468 0.0203 1.0000
17.750 1.0561 0.14876 0.14517 -0.0524 0.0205 1.0000
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Polar data table (+)
Polar graphs
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