EPPLER 557 AIRFOIL (e557-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 557 AIRFOIL (e557-il) Reynolds number: 200,000 Max Cl/Cd: 75.01 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e557-il-200000.txt Download as CSV file: xf-e557-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 557 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4515 0.10259 0.09893 -0.0565 1.0000 0.0314
-12.250 -0.6232 0.06840 0.06397 -0.0773 1.0000 0.0224
-12.000 -0.6413 0.06420 0.05969 -0.0782 1.0000 0.0223
-11.750 -0.6599 0.06054 0.05593 -0.0786 1.0000 0.0223
-11.500 -0.6727 0.05743 0.05277 -0.0779 1.0000 0.0220
-11.250 -0.7052 0.05449 0.04966 -0.0769 1.0000 0.0223
-11.000 -0.7211 0.05233 0.04746 -0.0747 1.0000 0.0222
-10.750 -0.7435 0.05050 0.04559 -0.0714 1.0000 0.0220
-10.500 -0.7730 0.04913 0.04414 -0.0678 1.0000 0.0221
-10.250 -0.7843 0.04693 0.04185 -0.0661 1.0000 0.0219
-10.000 -0.7896 0.04391 0.03842 -0.0673 0.9981 0.0223
-9.750 -0.7654 0.03987 0.03394 -0.0721 0.9933 0.0228
-9.500 -0.7364 0.03808 0.03221 -0.0745 0.9886 0.0239
-9.250 -0.7049 0.03573 0.02963 -0.0779 0.9845 0.0250
-9.000 -0.6776 0.03334 0.02694 -0.0797 0.9791 0.0255
-8.750 -0.6452 0.03121 0.02447 -0.0820 0.9748 0.0266
-8.500 -0.6155 0.02932 0.02255 -0.0833 0.9708 0.0281
-8.250 -0.5854 0.02799 0.02120 -0.0847 0.9651 0.0299
-8.000 -0.5497 0.02652 0.01966 -0.0874 0.9617 0.0333
-7.750 -0.5208 0.02546 0.01858 -0.0888 0.9550 0.0373
-7.500 -0.4866 0.02395 0.01711 -0.0914 0.9505 0.0425
-7.250 -0.4462 0.02259 0.01576 -0.0953 0.9477 0.0516
-7.000 -0.4187 0.02138 0.01456 -0.0967 0.9397 0.0612
-6.750 -0.3786 0.01984 0.01310 -0.1009 0.9360 0.0793
-6.500 -0.3344 0.01818 0.01160 -0.1060 0.9337 0.1165
-6.250 -0.2978 0.01575 0.00998 -0.1111 0.9280 0.2554
-6.000 -0.2587 0.01548 0.01003 -0.1137 0.9230 0.3690
-5.750 -0.2159 0.01567 0.01012 -0.1162 0.9200 0.4011
-5.500 -0.1713 0.01587 0.01017 -0.1190 0.9180 0.4228
-5.250 -0.1453 0.01616 0.01046 -0.1182 0.9087 0.4343
-5.000 -0.1038 0.01626 0.01050 -0.1203 0.9057 0.4465
-4.750 -0.0586 0.01624 0.01035 -0.1234 0.9036 0.4586
-4.500 -0.0284 0.01642 0.01056 -0.1232 0.8960 0.4657
-4.250 0.0130 0.01636 0.01039 -0.1256 0.8915 0.4759
-4.000 0.0551 0.01664 0.01070 -0.1275 0.8882 0.4872
-3.750 0.0874 0.01662 0.01064 -0.1281 0.8805 0.4944
-3.500 0.1256 0.01641 0.01038 -0.1299 0.8744 0.4988
-3.250 0.1706 0.01602 0.00984 -0.1334 0.8700 0.5042
-3.000 0.1996 0.01574 0.00942 -0.1339 0.8595 0.5085
-2.750 0.2393 0.01549 0.00913 -0.1361 0.8536 0.5117
-2.500 0.2668 0.01536 0.00895 -0.1359 0.8429 0.5149
-2.250 0.3013 0.01516 0.00865 -0.1373 0.8346 0.5189
-2.000 0.3340 0.01496 0.00829 -0.1385 0.8250 0.5239
-1.750 0.3633 0.01481 0.00810 -0.1387 0.8152 0.5267
-1.500 0.3958 0.01468 0.00791 -0.1395 0.8065 0.5297
-1.250 0.4227 0.01462 0.00782 -0.1393 0.7957 0.5332
-1.000 0.4552 0.01453 0.00761 -0.1402 0.7870 0.5378
-0.750 0.4836 0.01443 0.00742 -0.1405 0.7764 0.5420
-0.500 0.5113 0.01438 0.00736 -0.1403 0.7665 0.5448
-0.250 0.5413 0.01433 0.00726 -0.1407 0.7574 0.5482
0.000 0.5678 0.01432 0.00723 -0.1404 0.7467 0.5523
0.250 0.5989 0.01431 0.00709 -0.1411 0.7378 0.5573
0.500 0.6251 0.01427 0.00707 -0.1407 0.7273 0.5608
0.750 0.6523 0.01429 0.00709 -0.1405 0.7175 0.5643
1.000 0.6813 0.01430 0.00704 -0.1407 0.7083 0.5686
1.250 0.7082 0.01434 0.00704 -0.1406 0.6977 0.5734
1.500 0.7370 0.01436 0.00702 -0.1408 0.6888 0.5774
1.750 0.7624 0.01440 0.00711 -0.1402 0.6783 0.5816
2.000 0.7896 0.01447 0.00716 -0.1401 0.6685 0.5866
2.250 0.8186 0.01453 0.00713 -0.1403 0.6591 0.5919
2.500 0.8433 0.01457 0.00726 -0.1397 0.6486 0.5957
2.750 0.8712 0.01466 0.00733 -0.1396 0.6394 0.6006
3.000 0.8972 0.01475 0.00741 -0.1393 0.6288 0.6066
3.250 0.9230 0.01484 0.00754 -0.1389 0.6187 0.6116
3.500 0.9504 0.01494 0.00762 -0.1387 0.6091 0.6172
3.750 0.9751 0.01505 0.00776 -0.1381 0.5979 0.6235
4.000 1.0008 0.01515 0.00789 -0.1377 0.5877 0.6287
4.250 1.0267 0.01526 0.00801 -0.1372 0.5773 0.6350
4.500 1.0510 0.01539 0.00819 -0.1366 0.5660 0.6423
4.750 1.0758 0.01552 0.00837 -0.1359 0.5555 0.6487
5.000 1.1013 0.01568 0.00851 -0.1355 0.5448 0.6570
5.250 1.1240 0.01580 0.00874 -0.1345 0.5333 0.6636
5.500 1.1486 0.01598 0.00895 -0.1339 0.5225 0.6724
5.750 1.1725 0.01615 0.00914 -0.1331 0.5115 0.6806
6.000 1.1945 0.01632 0.00939 -0.1320 0.4994 0.6910
6.250 1.2164 0.01650 0.00967 -0.1308 0.4878 0.7003
6.500 1.2389 0.01670 0.00989 -0.1298 0.4761 0.7112
6.750 1.2603 0.01691 0.01015 -0.1286 0.4635 0.7237
7.000 1.2796 0.01710 0.01047 -0.1270 0.4506 0.7363
7.250 1.2988 0.01732 0.01079 -0.1254 0.4377 0.7509
7.500 1.3172 0.01756 0.01110 -0.1236 0.4245 0.7676
7.750 1.3346 0.01782 0.01142 -0.1217 0.4110 0.7872
8.000 1.3496 0.01808 0.01176 -0.1193 0.3971 0.8096
8.250 1.3614 0.01830 0.01211 -0.1162 0.3828 0.8409
8.500 1.3630 0.01830 0.01230 -0.1110 0.3698 0.9130
8.750 1.3765 0.01868 0.01266 -0.1088 0.3538 1.0000
9.000 1.3899 0.01925 0.01318 -0.1066 0.3369 1.0000
9.250 1.4012 0.01990 0.01379 -0.1041 0.3197 1.0000
9.500 1.4108 0.02063 0.01447 -0.1015 0.3020 1.0000
9.750 1.4197 0.02142 0.01524 -0.0988 0.2835 1.0000
10.000 1.4270 0.02233 0.01612 -0.0960 0.2649 1.0000
10.250 1.4327 0.02339 0.01713 -0.0932 0.2468 1.0000
10.500 1.4373 0.02459 0.01828 -0.0904 0.2296 1.0000
10.750 1.4411 0.02591 0.01955 -0.0877 0.2135 1.0000
11.000 1.4445 0.02735 0.02095 -0.0852 0.1983 1.0000
11.250 1.4476 0.02890 0.02248 -0.0829 0.1842 1.0000
11.500 1.4503 0.03056 0.02413 -0.0807 0.1710 1.0000
11.750 1.4523 0.03237 0.02593 -0.0786 0.1589 1.0000
12.000 1.4529 0.03438 0.02791 -0.0767 0.1481 1.0000
12.250 1.4532 0.03652 0.03005 -0.0750 0.1378 1.0000
12.500 1.4557 0.03858 0.03216 -0.0736 0.1277 1.0000
12.750 1.4554 0.04098 0.03457 -0.0723 0.1191 1.0000
13.000 1.4545 0.04353 0.03712 -0.0711 0.1111 1.0000
13.250 1.4557 0.04600 0.03967 -0.0702 0.1033 1.0000
13.500 1.4521 0.04902 0.04265 -0.0693 0.0971 1.0000
13.750 1.4540 0.05164 0.04539 -0.0688 0.0903 1.0000
14.000 1.4499 0.05494 0.04866 -0.0683 0.0849 1.0000
14.250 1.4509 0.05784 0.05169 -0.0680 0.0794 1.0000
14.500 1.4483 0.06120 0.05508 -0.0680 0.0747 1.0000
14.750 1.4469 0.06454 0.05849 -0.0679 0.0702 1.0000
15.000 1.4462 0.06790 0.06195 -0.0681 0.0659 1.0000
15.250 1.4424 0.07159 0.06556 -0.0682 0.0622 1.0000
15.500 1.4426 0.07507 0.06925 -0.0688 0.0587 1.0000
15.750 1.4411 0.07879 0.07303 -0.0695 0.0555 1.0000
16.000 1.4394 0.08240 0.07660 -0.0698 0.0524 1.0000
16.250 1.4382 0.08629 0.08069 -0.0708 0.0497 1.0000
16.500 1.4369 0.09017 0.08464 -0.0718 0.0472 1.0000
16.750 1.4381 0.09340 0.08779 -0.0722 0.0445 1.0000
17.000 1.4349 0.09781 0.09243 -0.0737 0.0426 1.0000
17.250 1.4330 0.10194 0.09669 -0.0751 0.0406 1.0000
17.500 1.4325 0.10578 0.10056 -0.0765 0.0388 1.0000
17.750 1.4342 0.10908 0.10387 -0.0772 0.0368 1.0000
18.000 1.4300 0.11382 0.10882 -0.0792 0.0353 1.0000
18.250 1.4276 0.11817 0.11329 -0.0812 0.0338 1.0000
18.500 1.4282 0.12187 0.11701 -0.0828 0.0323 1.0000
18.750 1.4306 0.12504 0.12019 -0.0839 0.0308 1.0000
19.000 1.4238 0.13041 0.12580 -0.0867 0.0298 1.0000
19.250 1.4188 0.13542 0.13097 -0.0895 0.0286 1.0000
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Polar data table (+)
Polar graphs
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