EPPLER 66 AIRFOIL (e66-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 66 AIRFOIL (e66-il) Reynolds number: 50,000 Max Cl/Cd: 40.72 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e66-il-50000-n5.txt Download as CSV file: xf-e66-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 66 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3799 0.10206 0.09533 -0.0388 1.0000 0.0505
-8.250 -0.3872 0.09918 0.09255 -0.0382 1.0000 0.0504
-8.000 -0.3959 0.09641 0.08989 -0.0374 1.0000 0.0498
-7.750 -0.4071 0.09375 0.08734 -0.0363 1.0000 0.0496
-7.500 -0.4205 0.09123 0.08494 -0.0349 1.0000 0.0491
-7.250 -0.4333 0.08830 0.08213 -0.0342 1.0000 0.0485
-7.000 -0.4435 0.08454 0.07847 -0.0352 1.0000 0.0479
-6.750 -0.4518 0.07993 0.07394 -0.0375 1.0000 0.0472
-6.250 -0.4611 0.06328 0.05701 -0.0516 1.0000 0.0442
-6.000 -0.4531 0.05750 0.05094 -0.0555 1.0000 0.0441
-5.750 -0.4395 0.05226 0.04534 -0.0588 1.0000 0.0444
-5.500 -0.4212 0.04779 0.04051 -0.0616 1.0000 0.0453
-5.250 -0.4007 0.04461 0.03704 -0.0634 1.0000 0.0473
-5.000 -0.3756 0.04120 0.03311 -0.0658 1.0000 0.0514
-4.750 -0.3432 0.03705 0.02797 -0.0689 0.9996 0.0551
-4.500 -0.3082 0.03448 0.02508 -0.0717 0.9962 0.0592
-4.250 -0.2715 0.03257 0.02255 -0.0741 0.9926 0.0680
-4.000 -0.2380 0.03095 0.02080 -0.0759 0.9886 0.0748
-3.750 -0.2028 0.02975 0.01936 -0.0778 0.9847 0.0876
-3.500 -0.1700 0.02865 0.01806 -0.0791 0.9801 0.1028
-3.250 -0.1363 0.02783 0.01717 -0.0808 0.9753 0.1288
-3.000 -0.1005 0.02720 0.01649 -0.0829 0.9710 0.1674
-2.750 -0.0682 0.02663 0.01599 -0.0844 0.9652 0.2122
-2.500 -0.0321 0.02622 0.01566 -0.0867 0.9605 0.2704
-2.250 -0.0005 0.02586 0.01547 -0.0880 0.9544 0.3337
-2.000 0.0330 0.02561 0.01540 -0.0894 0.9489 0.4082
-1.750 0.0638 0.02542 0.01542 -0.0902 0.9428 0.4874
-1.500 0.0925 0.02526 0.01545 -0.0903 0.9362 0.5702
-1.250 0.1187 0.02513 0.01553 -0.0895 0.9296 0.6569
-1.000 0.1397 0.02496 0.01555 -0.0875 0.9220 0.7470
-0.750 0.1588 0.02469 0.01541 -0.0850 0.9141 0.8672
-0.500 0.1978 0.02461 0.01510 -0.0876 0.9063 1.0000
-0.250 0.2288 0.02488 0.01509 -0.0889 0.8979 1.0000
0.000 0.2673 0.02515 0.01507 -0.0913 0.8917 1.0000
0.250 0.2957 0.02544 0.01517 -0.0920 0.8826 1.0000
0.500 0.3349 0.02567 0.01521 -0.0944 0.8768 1.0000
0.750 0.3612 0.02597 0.01536 -0.0946 0.8667 1.0000
1.000 0.3939 0.02622 0.01549 -0.0958 0.8588 1.0000
1.250 0.4268 0.02645 0.01562 -0.0970 0.8506 1.0000
1.500 0.4549 0.02673 0.01583 -0.0974 0.8408 1.0000
1.750 0.4933 0.02682 0.01586 -0.0993 0.8344 1.0000
2.000 0.5190 0.02713 0.01613 -0.0991 0.8233 1.0000
2.250 0.5482 0.02735 0.01633 -0.0995 0.8134 1.0000
2.500 0.5858 0.02733 0.01632 -0.1010 0.8063 1.0000
2.750 0.6117 0.02758 0.01659 -0.1008 0.7948 1.0000
3.000 0.6405 0.02774 0.01678 -0.1009 0.7841 1.0000
3.250 0.6804 0.02751 0.01662 -0.1025 0.7772 1.0000
3.500 0.7066 0.02769 0.01687 -0.1021 0.7649 1.0000
3.750 0.7344 0.02780 0.01706 -0.1019 0.7528 1.0000
4.000 0.7643 0.02782 0.01720 -0.1019 0.7410 1.0000
4.250 0.7973 0.02769 0.01718 -0.1022 0.7297 1.0000
4.500 0.8369 0.02730 0.01691 -0.1034 0.7196 1.0000
4.750 0.8670 0.02721 0.01699 -0.1032 0.7056 1.0000
5.000 0.8983 0.02706 0.01698 -0.1031 0.6911 1.0000
5.250 0.9240 0.02709 0.01715 -0.1022 0.6739 1.0000
5.500 0.9509 0.02707 0.01727 -0.1014 0.6559 1.0000
5.750 0.9812 0.02688 0.01728 -0.1009 0.6371 1.0000
6.000 1.0106 0.02673 0.01727 -0.1002 0.6164 1.0000
6.250 1.0366 0.02673 0.01739 -0.0991 0.5927 1.0000
6.500 1.0605 0.02683 0.01759 -0.0977 0.5664 1.0000
6.750 1.0840 0.02697 0.01786 -0.0962 0.5378 1.0000
7.000 1.1058 0.02722 0.01816 -0.0946 0.5065 1.0000
7.250 1.1251 0.02763 0.01855 -0.0926 0.4733 1.0000
7.500 1.1395 0.02824 0.01917 -0.0900 0.4384 1.0000
7.750 1.1527 0.02898 0.01983 -0.0874 0.4026 1.0000
8.000 1.1626 0.02992 0.02073 -0.0845 0.3664 1.0000
8.250 1.1712 0.03104 0.02177 -0.0816 0.3308 1.0000
8.500 1.1781 0.03232 0.02299 -0.0788 0.2961 1.0000
8.750 1.1837 0.03378 0.02435 -0.0760 0.2632 1.0000
9.000 1.1887 0.03540 0.02587 -0.0733 0.2332 1.0000
9.250 1.1930 0.03716 0.02756 -0.0708 0.2054 1.0000
9.500 1.1976 0.03906 0.02941 -0.0685 0.1804 1.0000
9.750 1.2006 0.04113 0.03140 -0.0663 0.1583 1.0000
10.000 1.2045 0.04329 0.03356 -0.0643 0.1380 1.0000
10.250 1.2067 0.04561 0.03582 -0.0625 0.1211 1.0000
10.500 1.2097 0.04802 0.03827 -0.0608 0.1069 1.0000
10.750 1.2134 0.05048 0.04078 -0.0592 0.0942 1.0000
11.000 1.2188 0.05297 0.04340 -0.0578 0.0833 1.0000
11.250 1.2247 0.05554 0.04612 -0.0565 0.0744 1.0000
11.500 1.2310 0.05816 0.04868 -0.0553 0.0684 1.0000
11.750 1.2407 0.06084 0.05174 -0.0541 0.0618 1.0000
12.000 1.2443 0.06362 0.05452 -0.0532 0.0573 1.0000
12.250 1.2525 0.06677 0.05804 -0.0522 0.0532 1.0000
12.500 1.2588 0.07018 0.06177 -0.0513 0.0503 1.0000
12.750 1.2602 0.07365 0.06545 -0.0506 0.0480 1.0000
13.000 1.2636 0.07698 0.06883 -0.0502 0.0455 1.0000
13.250 1.2536 0.08181 0.07406 -0.0503 0.0443 1.0000
13.500 1.2409 0.08710 0.07974 -0.0510 0.0433 1.0000
13.750 1.2260 0.09289 0.08587 -0.0524 0.0425 1.0000
14.000 1.2089 0.09930 0.09257 -0.0547 0.0421 1.0000
14.250 1.1897 0.10647 0.10001 -0.0579 0.0420 1.0000
14.500 1.1685 0.11459 0.10832 -0.0623 0.0422 1.0000
14.750 1.1462 0.12375 0.11767 -0.0678 0.0427 1.0000
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Polar data table (+)
Polar graphs
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