EPPLER 555 AIRFOIL (e555-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 555 AIRFOIL (e555-il) Reynolds number: 200,000 Max Cl/Cd: 67.1 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e555-il-200000-n5.txt Download as CSV file: xf-e555-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.5993 0.11346 0.10930 -0.0439 1.0000 0.0093
-15.000 -0.6457 0.09864 0.09419 -0.0520 1.0000 0.0091
-14.750 -0.6711 0.08974 0.08509 -0.0568 1.0000 0.0090
-14.500 -0.6897 0.08280 0.07794 -0.0603 1.0000 0.0089
-14.250 -0.7048 0.07691 0.07188 -0.0630 1.0000 0.0089
-14.000 -0.7162 0.07194 0.06675 -0.0652 1.0000 0.0089
-13.750 -0.7257 0.06753 0.06218 -0.0668 1.0000 0.0090
-13.500 -0.7332 0.06359 0.05808 -0.0680 1.0000 0.0089
-13.250 -0.7392 0.06014 0.05449 -0.0688 1.0000 0.0090
-13.000 -0.7429 0.05709 0.05132 -0.0692 1.0000 0.0091
-12.750 -0.7457 0.05424 0.04834 -0.0694 1.0000 0.0092
-12.500 -0.7473 0.05163 0.04561 -0.0693 1.0000 0.0093
-12.250 -0.7472 0.04931 0.04318 -0.0689 1.0000 0.0093
-12.000 -0.7469 0.04710 0.04086 -0.0684 1.0000 0.0095
-11.750 -0.7459 0.04506 0.03872 -0.0675 1.0000 0.0097
-11.500 -0.7443 0.04320 0.03678 -0.0665 1.0000 0.0098
-11.250 -0.7426 0.04147 0.03496 -0.0653 1.0000 0.0099
-11.000 -0.7419 0.03979 0.03320 -0.0638 1.0000 0.0102
-10.750 -0.7421 0.03820 0.03154 -0.0621 1.0000 0.0104
-10.500 -0.7437 0.03670 0.02997 -0.0600 1.0000 0.0106
-10.250 -0.7481 0.03528 0.02852 -0.0575 1.0000 0.0107
-10.000 -0.7581 0.03388 0.02712 -0.0544 1.0000 0.0108
-9.750 -0.7562 0.03230 0.02551 -0.0537 0.9977 0.0111
-9.500 -0.7344 0.03049 0.02364 -0.0568 0.9915 0.0116
-9.250 -0.7095 0.02867 0.02171 -0.0602 0.9849 0.0123
-9.000 -0.6852 0.02698 0.01988 -0.0630 0.9772 0.0134
-8.750 -0.6581 0.02540 0.01827 -0.0660 0.9707 0.0147
-8.500 -0.6333 0.02402 0.01679 -0.0679 0.9628 0.0162
-8.250 -0.6068 0.02271 0.01542 -0.0699 0.9561 0.0180
-7.750 -0.5481 0.02033 0.01289 -0.0741 0.9445 0.0252
-7.500 -0.5220 0.01927 0.01182 -0.0753 0.9365 0.0316
-7.250 -0.4887 0.01821 0.01076 -0.0777 0.9322 0.0438
-7.000 -0.4607 0.01723 0.00985 -0.0791 0.9245 0.0623
-6.750 -0.4278 0.01611 0.00889 -0.0816 0.9190 0.0970
-6.500 -0.3937 0.01462 0.00775 -0.0849 0.9138 0.1704
-6.250 -0.3636 0.01300 0.00683 -0.0876 0.9059 0.3118
-6.000 -0.3242 0.01274 0.00667 -0.0902 0.9012 0.3716
-5.750 -0.2904 0.01269 0.00655 -0.0914 0.8933 0.3966
-5.500 -0.2520 0.01266 0.00638 -0.0935 0.8870 0.4161
-5.250 -0.2167 0.01269 0.00630 -0.0949 0.8792 0.4301
-5.000 -0.1803 0.01275 0.00629 -0.0965 0.8714 0.4416
-4.750 -0.1469 0.01291 0.00638 -0.0974 0.8623 0.4549
-4.500 -0.1116 0.01293 0.00623 -0.0989 0.8536 0.4644
-4.250 -0.0814 0.01285 0.00609 -0.0993 0.8430 0.4673
-4.000 -0.0492 0.01276 0.00590 -0.1001 0.8332 0.4703
-3.750 -0.0182 0.01267 0.00569 -0.1007 0.8227 0.4737
-3.500 0.0117 0.01258 0.00546 -0.1012 0.8120 0.4771
-3.250 0.0425 0.01249 0.00523 -0.1018 0.8020 0.4800
-3.000 0.0716 0.01243 0.00511 -0.1020 0.7912 0.4823
-2.750 0.1003 0.01240 0.00501 -0.1021 0.7806 0.4851
-2.500 0.1297 0.01237 0.00488 -0.1024 0.7705 0.4880
-2.250 0.1579 0.01233 0.00475 -0.1025 0.7596 0.4910
-2.000 0.1864 0.01230 0.00462 -0.1026 0.7489 0.4940
-1.750 0.2152 0.01228 0.00451 -0.1027 0.7388 0.4969
-1.500 0.2425 0.01227 0.00447 -0.1026 0.7278 0.4994
-1.250 0.2703 0.01227 0.00443 -0.1025 0.7174 0.5022
-0.750 0.3259 0.01228 0.00431 -0.1025 0.6964 0.5082
-0.500 0.3539 0.01230 0.00425 -0.1025 0.6862 0.5114
-0.250 0.3814 0.01232 0.00423 -0.1024 0.6761 0.5141
0.000 0.4084 0.01235 0.00426 -0.1022 0.6656 0.5170
0.250 0.4358 0.01239 0.00427 -0.1021 0.6558 0.5201
0.500 0.4631 0.01243 0.00428 -0.1020 0.6455 0.5234
0.750 0.4905 0.01248 0.00429 -0.1019 0.6353 0.5267
1.000 0.5177 0.01254 0.00430 -0.1018 0.6257 0.5298
1.250 0.5444 0.01259 0.00438 -0.1015 0.6151 0.5328
1.500 0.5712 0.01266 0.00445 -0.1013 0.6051 0.5363
1.750 0.5981 0.01275 0.00451 -0.1011 0.5953 0.5401
2.000 0.6249 0.01283 0.00458 -0.1009 0.5847 0.5439
2.250 0.6515 0.01292 0.00468 -0.1007 0.5748 0.5470
2.500 0.6777 0.01301 0.00478 -0.1004 0.5643 0.5503
2.750 0.7040 0.01311 0.00491 -0.1001 0.5537 0.5543
3.000 0.7302 0.01324 0.00502 -0.0998 0.5432 0.5588
3.250 0.7560 0.01336 0.00515 -0.0994 0.5321 0.5629
3.500 0.7816 0.01347 0.00531 -0.0990 0.5206 0.5667
3.750 0.8070 0.01361 0.00548 -0.0985 0.5092 0.5709
4.000 0.8323 0.01378 0.00562 -0.0980 0.4979 0.5756
4.250 0.8575 0.01392 0.00581 -0.0976 0.4858 0.5801
4.500 0.8822 0.01408 0.00603 -0.0970 0.4739 0.5849
4.750 0.9067 0.01427 0.00623 -0.0964 0.4617 0.5904
5.000 0.9309 0.01448 0.00644 -0.0958 0.4495 0.5957
5.250 0.9547 0.01467 0.00670 -0.0950 0.4365 0.6006
5.500 0.9785 0.01488 0.00695 -0.0944 0.4236 0.6065
5.750 1.0019 0.01511 0.00721 -0.0936 0.4106 0.6125
6.000 1.0245 0.01535 0.00751 -0.0927 0.3973 0.6187
6.250 1.0467 0.01563 0.00781 -0.0917 0.3835 0.6261
6.500 1.0681 0.01592 0.00814 -0.0906 0.3691 0.6328
6.750 1.0891 0.01623 0.00849 -0.0895 0.3541 0.6406
7.000 1.1094 0.01656 0.00886 -0.0883 0.3384 0.6481
7.250 1.1290 0.01692 0.00925 -0.0869 0.3218 0.6568
7.500 1.1477 0.01731 0.00967 -0.0854 0.3045 0.6659
7.750 1.1654 0.01774 0.01013 -0.0838 0.2864 0.6764
8.000 1.1814 0.01819 0.01062 -0.0819 0.2681 0.6871
8.250 1.1948 0.01869 0.01113 -0.0796 0.2496 0.6986
8.750 1.2195 0.01989 0.01235 -0.0748 0.2134 0.7256
9.000 1.2309 0.02056 0.01305 -0.0724 0.1964 0.7420
9.250 1.2414 0.02128 0.01379 -0.0699 0.1806 0.7615
9.500 1.2509 0.02202 0.01459 -0.0673 0.1662 0.7858
9.750 1.2585 0.02279 0.01543 -0.0644 0.1527 0.8184
10.000 1.2613 0.02345 0.01624 -0.0607 0.1413 0.8873
10.250 1.2675 0.02434 0.01715 -0.0581 0.1299 1.0000
10.500 1.2771 0.02542 0.01823 -0.0563 0.1184 1.0000
10.750 1.2858 0.02659 0.01941 -0.0546 0.1086 1.0000
11.000 1.2931 0.02790 0.02071 -0.0528 0.0998 1.0000
11.250 1.2999 0.02929 0.02211 -0.0512 0.0913 1.0000
11.500 1.3071 0.03072 0.02359 -0.0497 0.0839 1.0000
11.750 1.3114 0.03242 0.02530 -0.0482 0.0773 1.0000
12.000 1.3181 0.03401 0.02695 -0.0470 0.0709 1.0000
12.250 1.3212 0.03595 0.02892 -0.0458 0.0656 1.0000
12.500 1.3264 0.03780 0.03084 -0.0448 0.0605 1.0000
12.750 1.3276 0.04009 0.03314 -0.0439 0.0561 1.0000
13.000 1.3322 0.04214 0.03530 -0.0432 0.0520 1.0000
13.250 1.3331 0.04463 0.03784 -0.0427 0.0483 1.0000
13.500 1.3346 0.04716 0.04047 -0.0423 0.0453 1.0000
13.750 1.3360 0.04977 0.04317 -0.0420 0.0421 1.0000
14.000 1.3343 0.05283 0.04629 -0.0420 0.0398 1.0000
14.250 1.3346 0.05578 0.04935 -0.0421 0.0374 1.0000
14.500 1.3341 0.05892 0.05260 -0.0423 0.0352 1.0000
14.750 1.3312 0.06247 0.05622 -0.0429 0.0333 1.0000
15.000 1.3281 0.06617 0.06002 -0.0436 0.0318 1.0000
15.250 1.3267 0.06975 0.06373 -0.0443 0.0301 1.0000
15.500 1.3236 0.07368 0.06777 -0.0453 0.0286 1.0000
15.750 1.3183 0.07804 0.07222 -0.0467 0.0274 1.0000
16.000 1.3128 0.08256 0.07683 -0.0482 0.0263 1.0000
16.250 1.3097 0.08681 0.08124 -0.0496 0.0251 1.0000
16.500 1.3054 0.09133 0.08589 -0.0513 0.0240 1.0000
16.750 1.2998 0.09618 0.09085 -0.0533 0.0230 1.0000
17.000 1.2926 0.10139 0.09615 -0.0555 0.0223 1.0000
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Polar data table (+)
Polar graphs
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