E203 (13.64%) (e203-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E203 (13.64%) (e203-il) Reynolds number: 100,000 Max Cl/Cd: 54.73 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e203-il-100000.txt Download as CSV file: xf-e203-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3886 0.10240 0.09744 -0.0403 1.0000 0.1482
-9.750 -0.4635 0.08076 0.07602 -0.0556 1.0000 0.0849
-9.500 -0.5048 0.06987 0.06519 -0.0624 1.0000 0.0754
-9.250 -0.5553 0.06434 0.05971 -0.0640 1.0000 0.0738
-9.000 -0.6427 0.05898 0.05382 -0.0611 1.0000 0.0696
-8.750 -0.6395 0.05554 0.05038 -0.0591 1.0000 0.0674
-8.500 -0.6484 0.05223 0.04697 -0.0566 1.0000 0.0663
-8.250 -0.6577 0.04903 0.04358 -0.0539 1.0000 0.0650
-8.000 -0.6651 0.04581 0.04010 -0.0513 1.0000 0.0638
-7.750 -0.6693 0.04257 0.03650 -0.0488 1.0000 0.0626
-7.500 -0.6685 0.03953 0.03303 -0.0466 1.0000 0.0617
-7.250 -0.6624 0.03694 0.03005 -0.0447 1.0000 0.0615
-7.000 -0.6524 0.03504 0.02785 -0.0431 1.0000 0.0626
-6.750 -0.6155 0.03266 0.02496 -0.0461 0.9942 0.0656
-6.500 -0.5766 0.03032 0.02213 -0.0487 0.9870 0.0676
-6.250 -0.5376 0.02805 0.01961 -0.0512 0.9808 0.0703
-6.000 -0.4992 0.02649 0.01807 -0.0538 0.9735 0.0765
-5.750 -0.4627 0.02505 0.01660 -0.0559 0.9657 0.0861
-5.500 -0.4244 0.02354 0.01520 -0.0583 0.9587 0.1034
-5.250 -0.3941 0.02186 0.01384 -0.0597 0.9497 0.1537
-5.000 -0.3564 0.02021 0.01280 -0.0629 0.9433 0.2557
-4.750 -0.3287 0.01963 0.01278 -0.0637 0.9329 0.3618
-4.500 -0.2934 0.01987 0.01305 -0.0650 0.9245 0.4360
-4.250 -0.2571 0.02010 0.01323 -0.0663 0.9165 0.4794
-4.000 -0.2259 0.02031 0.01336 -0.0667 0.9077 0.5131
-3.750 -0.1869 0.02042 0.01341 -0.0683 0.9014 0.5435
-3.500 -0.1569 0.02052 0.01352 -0.0683 0.8928 0.5659
-3.250 -0.1177 0.02046 0.01335 -0.0701 0.8870 0.5906
-3.000 -0.0853 0.02045 0.01332 -0.0705 0.8797 0.6093
-2.750 -0.0514 0.02036 0.01317 -0.0712 0.8728 0.6278
-2.500 -0.0134 0.02018 0.01293 -0.0726 0.8678 0.6460
-2.250 0.0117 0.02018 0.01288 -0.0720 0.8585 0.6611
-2.000 0.0515 0.01990 0.01253 -0.0737 0.8543 0.6775
-1.750 0.0723 0.01998 0.01259 -0.0724 0.8441 0.6907
-1.500 0.1099 0.01971 0.01227 -0.0738 0.8395 0.7055
-1.250 0.1304 0.01982 0.01235 -0.0726 0.8298 0.7187
-1.000 0.1657 0.01958 0.01207 -0.0735 0.8248 0.7332
-0.750 0.1860 0.01972 0.01221 -0.0723 0.8155 0.7470
-0.500 0.2189 0.01953 0.01198 -0.0729 0.8101 0.7618
-0.250 0.2391 0.01970 0.01217 -0.0716 0.8014 0.7764
0.000 0.2694 0.01956 0.01203 -0.0717 0.7956 0.7921
0.250 0.2903 0.01972 0.01222 -0.0705 0.7875 0.8086
0.500 0.3171 0.01967 0.01219 -0.0699 0.7812 0.8270
0.750 0.3399 0.01977 0.01233 -0.0689 0.7742 0.8485
1.000 0.3634 0.01982 0.01245 -0.0678 0.7671 0.8726
1.250 0.3999 0.01961 0.01225 -0.0686 0.7629 0.9004
1.500 0.4323 0.01998 0.01272 -0.0701 0.7537 0.9341
1.750 0.4961 0.01978 0.01250 -0.0769 0.7492 0.9626
2.000 0.5605 0.01997 0.01272 -0.0850 0.7416 0.9915
2.250 0.5806 0.02006 0.01274 -0.0852 0.7348 1.0000
2.500 0.5909 0.02068 0.01330 -0.0832 0.7262 1.0000
2.750 0.6182 0.02087 0.01344 -0.0833 0.7199 1.0000
3.000 0.6372 0.02146 0.01401 -0.0823 0.7119 1.0000
3.250 0.6648 0.02169 0.01423 -0.0823 0.7052 1.0000
3.500 0.6858 0.02223 0.01479 -0.0815 0.6973 1.0000
3.750 0.7133 0.02245 0.01501 -0.0814 0.6901 1.0000
4.000 0.7345 0.02296 0.01558 -0.0805 0.6817 1.0000
4.250 0.7642 0.02303 0.01566 -0.0805 0.6744 1.0000
4.500 0.7839 0.02359 0.01628 -0.0794 0.6650 1.0000
4.750 0.8179 0.02340 0.01612 -0.0797 0.6581 1.0000
5.000 0.8360 0.02398 0.01678 -0.0783 0.6476 1.0000
5.250 0.8726 0.02362 0.01643 -0.0788 0.6406 1.0000
5.500 0.8932 0.02394 0.01685 -0.0775 0.6293 1.0000
5.750 0.9165 0.02411 0.01713 -0.0765 0.6183 1.0000
6.000 0.9487 0.02377 0.01682 -0.0763 0.6084 1.0000
6.250 0.9790 0.02344 0.01655 -0.0759 0.5971 1.0000
6.500 1.0025 0.02339 0.01662 -0.0747 0.5839 1.0000
6.750 1.0280 0.02318 0.01649 -0.0736 0.5700 1.0000
7.000 1.0543 0.02283 0.01622 -0.0725 0.5553 1.0000
7.250 1.0809 0.02239 0.01584 -0.0714 0.5391 1.0000
7.500 1.1076 0.02189 0.01539 -0.0702 0.5216 1.0000
7.750 1.1254 0.02174 0.01537 -0.0680 0.5007 1.0000
8.000 1.1460 0.02139 0.01507 -0.0659 0.4775 1.0000
8.250 1.1601 0.02133 0.01509 -0.0631 0.4494 1.0000
8.500 1.1718 0.02141 0.01519 -0.0599 0.4152 1.0000
8.750 1.1777 0.02181 0.01548 -0.0560 0.3723 1.0000
9.000 1.1769 0.02267 0.01611 -0.0514 0.3212 1.0000
9.250 1.1690 0.02396 0.01705 -0.0461 0.2747 1.0000
9.500 1.1597 0.02566 0.01841 -0.0412 0.2344 1.0000
9.750 1.1510 0.02759 0.02004 -0.0369 0.2009 1.0000
10.000 1.1440 0.02964 0.02186 -0.0334 0.1723 1.0000
10.250 1.1390 0.03177 0.02383 -0.0305 0.1476 1.0000
10.500 1.1343 0.03407 0.02588 -0.0280 0.1280 1.0000
10.750 1.1326 0.03633 0.02812 -0.0260 0.1087 1.0000
11.000 1.1313 0.03873 0.03043 -0.0242 0.0929 1.0000
11.250 1.1317 0.04120 0.03283 -0.0225 0.0793 1.0000
11.500 1.1363 0.04357 0.03515 -0.0210 0.0683 1.0000
11.750 1.1455 0.04583 0.03738 -0.0196 0.0598 1.0000
12.000 1.1620 0.04781 0.03926 -0.0185 0.0540 1.0000
12.250 1.1856 0.05011 0.04174 -0.0174 0.0496 1.0000
12.500 1.1984 0.05238 0.04419 -0.0165 0.0465 1.0000
12.750 1.2171 0.05475 0.04649 -0.0160 0.0433 1.0000
13.000 1.2302 0.05826 0.05030 -0.0152 0.0418 1.0000
13.250 1.2315 0.06157 0.05395 -0.0141 0.0412 1.0000
13.500 1.2281 0.06522 0.05792 -0.0132 0.0408 1.0000
13.750 1.2199 0.06924 0.06226 -0.0126 0.0406 1.0000
14.000 1.2077 0.07366 0.06700 -0.0123 0.0404 1.0000
14.250 1.1941 0.07831 0.07192 -0.0126 0.0405 1.0000
14.500 1.1774 0.08344 0.07732 -0.0133 0.0407 1.0000
14.750 1.1572 0.08910 0.08324 -0.0148 0.0408 1.0000
15.000 1.1375 0.09504 0.08941 -0.0168 0.0411 1.0000
15.250 1.1152 0.10166 0.09625 -0.0196 0.0413 1.0000
15.500 1.0938 0.10866 0.10343 -0.0229 0.0416 1.0000
15.750 1.0724 0.11622 0.11115 -0.0269 0.0420 1.0000
16.000 1.0516 0.12438 0.11945 -0.0314 0.0424 1.0000
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Polar data table (+)
Polar graphs
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