EPPLER 555 AIRFOIL (e555-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 555 AIRFOIL (e555-il) Reynolds number: 100,000 Max Cl/Cd: 51.16 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e555-il-100000.txt Download as CSV file: xf-e555-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 555 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.4447 0.13586 0.13068 -0.0403 1.0000 0.1278
-12.500 -0.4934 0.10622 0.10108 -0.0538 1.0000 0.0629
-12.250 -0.5727 0.08732 0.08196 -0.0663 1.0000 0.0515
-12.000 -0.5868 0.08182 0.07645 -0.0681 1.0000 0.0509
-11.750 -0.6066 0.07645 0.07102 -0.0702 1.0000 0.0503
-11.500 -0.6260 0.07164 0.06614 -0.0717 1.0000 0.0495
-11.250 -0.6473 0.06704 0.06146 -0.0727 1.0000 0.0482
-11.000 -0.6725 0.06301 0.05730 -0.0729 1.0000 0.0476
-10.750 -0.6999 0.05962 0.05378 -0.0719 1.0000 0.0468
-10.500 -0.7298 0.05717 0.05120 -0.0689 1.0000 0.0462
-10.250 -0.7792 0.05456 0.04798 -0.0646 1.0000 0.0437
-10.000 -0.7851 0.05173 0.04496 -0.0624 1.0000 0.0439
-9.750 -0.7869 0.04896 0.04202 -0.0602 1.0000 0.0442
-9.500 -0.7835 0.04642 0.03939 -0.0583 1.0000 0.0448
-9.250 -0.7797 0.04409 0.03685 -0.0562 1.0000 0.0452
-9.000 -0.7741 0.04174 0.03427 -0.0542 1.0000 0.0453
-8.750 -0.7651 0.03953 0.03185 -0.0523 1.0000 0.0457
-8.500 -0.7536 0.03759 0.02975 -0.0504 1.0000 0.0464
-8.250 -0.7405 0.03583 0.02786 -0.0486 1.0000 0.0475
-8.000 -0.7265 0.03426 0.02615 -0.0467 1.0000 0.0492
-7.750 -0.7129 0.03307 0.02469 -0.0450 1.0000 0.0519
-7.500 -0.6997 0.03145 0.02329 -0.0431 1.0000 0.0556
-7.250 -0.6858 0.03038 0.02216 -0.0414 1.0000 0.0601
-7.000 -0.6735 0.02903 0.02095 -0.0393 1.0000 0.0654
-6.750 -0.6600 0.02798 0.01992 -0.0378 1.0000 0.0741
-6.500 -0.6471 0.02658 0.01873 -0.0366 1.0000 0.0877
-6.250 -0.6310 0.02492 0.01727 -0.0367 1.0000 0.1139
-6.000 -0.6061 0.02087 0.01528 -0.0418 1.0000 0.3762
-5.750 -0.5640 0.02369 0.01795 -0.0430 0.9919 0.4505
-5.500 -0.5235 0.02605 0.02020 -0.0437 0.9835 0.4778
-5.250 -0.4889 0.02797 0.02208 -0.0432 0.9742 0.4969
-5.000 -0.4562 0.02964 0.02370 -0.0423 0.9651 0.5131
-4.750 -0.4203 0.03096 0.02491 -0.0424 0.9570 0.5285
-4.500 -0.3915 0.03288 0.02691 -0.0390 0.9482 0.5367
-4.250 -0.3617 0.03353 0.02746 -0.0384 0.9391 0.5496
-4.000 -0.3218 0.03381 0.02758 -0.0402 0.9323 0.5636
-3.750 -0.2969 0.03423 0.02797 -0.0385 0.9225 0.5701
-3.500 -0.2503 0.03329 0.02680 -0.0438 0.9166 0.5800
-3.250 -0.2258 0.03324 0.02668 -0.0429 0.9063 0.5845
-3.000 -0.1763 0.03223 0.02545 -0.0488 0.9011 0.5927
-2.750 -0.1499 0.03172 0.02485 -0.0494 0.8905 0.5971
-2.500 -0.1054 0.03130 0.02434 -0.0523 0.8856 0.6015
-2.250 -0.0763 0.03068 0.02360 -0.0541 0.8749 0.6068
-2.000 -0.0246 0.02965 0.02239 -0.0599 0.8703 0.6121
-1.750 0.0005 0.02944 0.02216 -0.0595 0.8598 0.6154
-1.500 0.0485 0.02876 0.02139 -0.0633 0.8551 0.6196
-1.250 0.0852 0.02812 0.02064 -0.0663 0.8462 0.6245
-1.000 0.1320 0.02742 0.01986 -0.0702 0.8403 0.6292
-0.750 0.1824 0.02678 0.01918 -0.0739 0.8367 0.6329
-0.500 0.2078 0.02650 0.01886 -0.0741 0.8248 0.6368
-0.250 0.2635 0.02558 0.01782 -0.0799 0.8207 0.6428
0.000 0.2854 0.02545 0.01771 -0.0789 0.8087 0.6462
0.250 0.3221 0.02507 0.01731 -0.0803 0.8009 0.6502
0.500 0.3578 0.02465 0.01686 -0.0821 0.7917 0.6547
0.750 0.3925 0.02430 0.01644 -0.0841 0.7817 0.6601
1.000 0.4287 0.02390 0.01607 -0.0850 0.7739 0.6639
1.250 0.4536 0.02384 0.01603 -0.0846 0.7623 0.6686
1.500 0.4994 0.02329 0.01538 -0.0880 0.7557 0.6743
1.750 0.5218 0.02327 0.01541 -0.0872 0.7431 0.6784
2.000 0.5477 0.02323 0.01541 -0.0868 0.7323 0.6830
2.250 0.5870 0.02287 0.01500 -0.0888 0.7240 0.6893
2.500 0.6106 0.02291 0.01508 -0.0883 0.7117 0.6943
2.750 0.6372 0.02287 0.01509 -0.0879 0.7009 0.6991
3.000 0.6738 0.02262 0.01479 -0.0894 0.6918 0.7054
3.250 0.6968 0.02270 0.01495 -0.0887 0.6793 0.7111
3.500 0.7225 0.02273 0.01503 -0.0882 0.6682 0.7171
3.750 0.7602 0.02250 0.01474 -0.0899 0.6587 0.7246
4.000 0.7804 0.02261 0.01497 -0.0884 0.6459 0.7299
4.250 0.8061 0.02268 0.01510 -0.0881 0.6338 0.7373
4.500 0.8342 0.02263 0.01509 -0.0879 0.6227 0.7445
4.750 0.8636 0.02256 0.01503 -0.0879 0.6114 0.7528
5.000 0.8859 0.02267 0.01524 -0.0869 0.5984 0.7605
5.250 0.9107 0.02275 0.01540 -0.0863 0.5859 0.7693
5.500 0.9368 0.02274 0.01544 -0.0857 0.5740 0.7782
5.750 0.9675 0.02266 0.01534 -0.0859 0.5621 0.7892
6.000 0.9867 0.02276 0.01558 -0.0842 0.5484 0.7998
6.250 1.0080 0.02284 0.01577 -0.0828 0.5348 0.8113
6.500 1.0303 0.02291 0.01591 -0.0816 0.5213 0.8244
6.750 1.0520 0.02293 0.01601 -0.0803 0.5076 0.8394
7.000 1.0725 0.02291 0.01606 -0.0786 0.4940 0.8569
7.250 1.0918 0.02285 0.01605 -0.0766 0.4802 0.8785
7.500 1.1078 0.02270 0.01598 -0.0739 0.4662 0.9076
7.750 1.1314 0.02257 0.01599 -0.0732 0.4493 1.0000
8.000 1.1614 0.02298 0.01645 -0.0748 0.4292 1.0000
8.250 1.1887 0.02334 0.01679 -0.0754 0.4089 1.0000
8.500 1.2129 0.02371 0.01707 -0.0752 0.3889 1.0000
8.750 1.2320 0.02418 0.01751 -0.0741 0.3686 1.0000
9.000 1.2464 0.02473 0.01806 -0.0722 0.3473 1.0000
9.250 1.2602 0.02531 0.01857 -0.0701 0.3264 1.0000
9.500 1.2707 0.02603 0.01923 -0.0677 0.3053 1.0000
9.750 1.2772 0.02683 0.02001 -0.0646 0.2847 1.0000
10.000 1.2821 0.02771 0.02083 -0.0614 0.2653 1.0000
10.250 1.2876 0.02878 0.02173 -0.0584 0.2466 1.0000
10.500 1.2900 0.02999 0.02294 -0.0553 0.2284 1.0000
10.750 1.2927 0.03135 0.02426 -0.0524 0.2112 1.0000
11.000 1.2955 0.03284 0.02570 -0.0498 0.1953 1.0000
11.250 1.2984 0.03446 0.02727 -0.0474 0.1806 1.0000
11.500 1.3012 0.03619 0.02895 -0.0453 0.1670 1.0000
11.750 1.3049 0.03801 0.03073 -0.0434 0.1545 1.0000
12.000 1.3105 0.03989 0.03248 -0.0418 0.1427 1.0000
12.250 1.3106 0.04192 0.03465 -0.0400 0.1327 1.0000
12.500 1.3144 0.04409 0.03687 -0.0385 0.1231 1.0000
12.750 1.3220 0.04617 0.03885 -0.0375 0.1140 1.0000
13.000 1.3219 0.04853 0.04137 -0.0362 0.1066 1.0000
13.250 1.3283 0.05090 0.04375 -0.0352 0.0992 1.0000
13.500 1.3301 0.05333 0.04627 -0.0343 0.0930 1.0000
13.750 1.3365 0.05594 0.04894 -0.0336 0.0869 1.0000
14.000 1.3345 0.05880 0.05198 -0.0328 0.0822 1.0000
14.250 1.3479 0.06122 0.05430 -0.0324 0.0765 1.0000
14.500 1.3389 0.06480 0.05821 -0.0319 0.0735 1.0000
14.750 1.3363 0.06800 0.06156 -0.0317 0.0701 1.0000
15.000 1.3502 0.07071 0.06417 -0.0314 0.0657 1.0000
15.250 1.3349 0.07520 0.06902 -0.0317 0.0642 1.0000
15.500 1.3213 0.07986 0.07398 -0.0324 0.0624 1.0000
15.750 1.3103 0.08444 0.07878 -0.0334 0.0606 1.0000
16.000 1.3029 0.08876 0.08325 -0.0345 0.0588 1.0000
16.250 1.3125 0.09212 0.08653 -0.0346 0.0559 1.0000
16.500 1.2889 0.09855 0.09327 -0.0372 0.0557 1.0000
16.750 1.2642 0.10567 0.10069 -0.0405 0.0555 1.0000
17.000 1.2385 0.11349 0.10878 -0.0447 0.0555 1.0000
17.250 1.2113 0.12212 0.11765 -0.0497 0.0557 1.0000
17.500 1.1828 0.13164 0.12737 -0.0557 0.0560 1.0000
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Polar data table (+)
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