EPPLER 639 AIRFOIL (e639-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 639 AIRFOIL (e639-il) Reynolds number: 200,000 Max Cl/Cd: 62.73 at α=11.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e639-il-200000.txt Download as CSV file: xf-e639-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 639 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.1834 0.09107 0.08826 -0.0332 1.0000 0.0356
-9.000 -0.1815 0.08804 0.08530 -0.0334 1.0000 0.0362
-8.750 -0.2719 0.09386 0.09083 -0.0349 1.0000 0.0341
-8.500 -0.2632 0.09097 0.08799 -0.0334 1.0000 0.0348
-8.250 -0.2608 0.08827 0.08536 -0.0333 1.0000 0.0354
-8.000 -0.2609 0.08569 0.08288 -0.0334 1.0000 0.0360
-7.750 -0.2327 0.08035 0.07753 -0.0424 0.9421 0.0377
-7.500 -0.1924 0.07281 0.06977 -0.0606 0.8814 0.0405
-7.250 -0.1817 0.06863 0.06516 -0.0701 0.8307 0.0417
-7.000 -0.1803 0.06621 0.06235 -0.0712 0.7997 0.0420
-6.750 -0.1729 0.06074 0.05691 -0.0704 0.7773 0.0429
-6.500 -0.1628 0.05828 0.05436 -0.0691 0.7558 0.0439
-6.250 -0.1530 0.05593 0.05187 -0.0685 0.7370 0.0452
-6.000 -0.1425 0.05342 0.04919 -0.0682 0.7210 0.0472
-5.750 -0.1296 0.05087 0.04639 -0.0683 0.7067 0.0503
-5.500 -0.1197 0.04801 0.04295 -0.0677 0.6955 0.0534
-5.250 -0.1059 0.04485 0.03985 -0.0672 0.6825 0.0552
-5.000 -0.0901 0.04285 0.03776 -0.0664 0.6693 0.0578
-4.750 -0.0719 0.04096 0.03562 -0.0656 0.6574 0.0622
-4.500 -0.0560 0.03854 0.03267 -0.0641 0.6478 0.0670
-4.250 -0.0382 0.03610 0.03021 -0.0635 0.6371 0.0692
-4.000 -0.0185 0.03441 0.02838 -0.0626 0.6264 0.0733
-3.750 0.0013 0.03285 0.02630 -0.0611 0.6180 0.0817
-3.500 0.0216 0.03079 0.02423 -0.0605 0.6083 0.0853
-3.250 0.0428 0.02963 0.02266 -0.0591 0.5995 0.0971
-3.000 0.0646 0.02783 0.02083 -0.0585 0.5911 0.1024
-2.750 0.0861 0.02652 0.01935 -0.0576 0.5824 0.1174
-2.500 0.1082 0.02539 0.01804 -0.0568 0.5752 0.1353
-2.000 0.1754 0.02120 0.01232 -0.0525 0.5616 0.0528
-1.750 0.2022 0.01924 0.01023 -0.0520 0.5548 0.0502
-1.500 0.2294 0.01820 0.00903 -0.0514 0.5476 0.0492
-1.250 0.2564 0.01760 0.00826 -0.0508 0.5414 0.0503
-1.000 0.2830 0.01713 0.00772 -0.0502 0.5346 0.0519
-0.750 0.3092 0.01658 0.00708 -0.0496 0.5292 0.0524
-0.500 0.3330 0.01591 0.00644 -0.0487 0.5232 0.0541
-0.250 0.3570 0.01549 0.00602 -0.0478 0.5173 0.0574
0.000 0.3823 0.01533 0.00573 -0.0471 0.5125 0.0637
0.250 0.5386 0.01280 0.00560 -0.0719 0.5013 1.0000
0.500 0.5621 0.01295 0.00555 -0.0712 0.4970 1.0000
0.750 0.5846 0.01304 0.00561 -0.0702 0.4915 1.0000
1.000 0.6076 0.01316 0.00561 -0.0694 0.4866 1.0000
1.250 0.6312 0.01334 0.00563 -0.0686 0.4828 1.0000
1.500 0.6537 0.01350 0.00578 -0.0677 0.4782 1.0000
1.750 0.6765 0.01366 0.00589 -0.0669 0.4736 1.0000
2.000 0.6999 0.01383 0.00595 -0.0661 0.4696 1.0000
2.250 0.7233 0.01406 0.00610 -0.0653 0.4659 1.0000
2.500 0.7453 0.01425 0.00631 -0.0643 0.4613 1.0000
2.750 0.7683 0.01445 0.00647 -0.0635 0.4574 1.0000
3.000 0.7920 0.01467 0.00661 -0.0628 0.4540 1.0000
3.250 0.8152 0.01495 0.00684 -0.0620 0.4504 1.0000
3.500 0.8368 0.01517 0.00712 -0.0609 0.4461 1.0000
3.750 0.8596 0.01541 0.00733 -0.0601 0.4423 1.0000
4.000 0.8834 0.01566 0.00753 -0.0594 0.4391 1.0000
4.250 0.9073 0.01600 0.00780 -0.0588 0.4361 1.0000
4.500 0.9280 0.01626 0.00818 -0.0576 0.4319 1.0000
4.750 0.9503 0.01652 0.00847 -0.0567 0.4280 1.0000
5.000 0.9739 0.01679 0.00870 -0.0560 0.4248 1.0000
5.250 0.9989 0.01714 0.00897 -0.0556 0.4220 1.0000
5.500 1.0190 0.01749 0.00945 -0.0544 0.4182 1.0000
5.750 1.0402 0.01779 0.00983 -0.0533 0.4141 1.0000
6.000 1.0633 0.01807 0.01013 -0.0526 0.4108 1.0000
6.250 1.0881 0.01838 0.01039 -0.0522 0.4080 1.0000
6.500 1.1096 0.01880 0.01087 -0.0512 0.4045 1.0000
6.750 1.1293 0.01917 0.01139 -0.0500 0.4004 1.0000
7.000 1.1515 0.01948 0.01175 -0.0491 0.3968 1.0000
7.250 1.1762 0.01975 0.01199 -0.0487 0.3937 1.0000
7.500 1.1991 0.02017 0.01245 -0.0480 0.3903 1.0000
7.750 1.2168 0.02058 0.01304 -0.0465 0.3858 1.0000
8.000 1.2385 0.02085 0.01337 -0.0456 0.3818 1.0000
8.250 1.2640 0.02106 0.01354 -0.0453 0.3783 1.0000
8.500 1.2840 0.02149 0.01410 -0.0442 0.3743 1.0000
8.750 1.3018 0.02184 0.01460 -0.0427 0.3694 1.0000
9.000 1.3251 0.02200 0.01478 -0.0421 0.3652 1.0000
9.250 1.3509 0.02225 0.01500 -0.0419 0.3612 1.0000
9.500 1.3644 0.02266 0.01566 -0.0398 0.3558 1.0000
9.750 1.3860 0.02283 0.01588 -0.0390 0.3512 1.0000
10.000 1.4139 0.02298 0.01596 -0.0391 0.3471 1.0000
10.250 1.4242 0.02343 0.01670 -0.0366 0.3413 1.0000
10.500 1.4453 0.02351 0.01684 -0.0356 0.3360 1.0000
10.750 1.4660 0.02368 0.01705 -0.0346 0.3307 1.0000
11.000 1.4783 0.02396 0.01752 -0.0324 0.3243 1.0000
11.250 1.5018 0.02394 0.01748 -0.0318 0.3188 1.0000
11.500 1.5099 0.02440 0.01817 -0.0291 0.3125 1.0000
11.750 1.5261 0.02449 0.01832 -0.0274 0.3062 1.0000
12.000 1.5356 0.02487 0.01884 -0.0249 0.2996 1.0000
12.250 1.5434 0.02510 0.01917 -0.0221 0.2925 1.0000
12.500 1.5463 0.02552 0.01969 -0.0185 0.2856 1.0000
12.750 1.5475 0.02596 0.02022 -0.0151 0.2777 1.0000
13.000 1.5452 0.02678 0.02118 -0.0117 0.2692 1.0000
13.250 1.5449 0.02767 0.02208 -0.0090 0.2601 1.0000
13.500 1.5391 0.02912 0.02364 -0.0066 0.2498 1.0000
13.750 1.5331 0.03097 0.02560 -0.0047 0.2392 1.0000
14.000 1.5250 0.03326 0.02795 -0.0034 0.2280 1.0000
14.250 1.5153 0.03601 0.03072 -0.0024 0.2171 1.0000
14.500 1.5027 0.03927 0.03399 -0.0019 0.2059 1.0000
14.750 1.4891 0.04292 0.03770 -0.0018 0.1950 1.0000
15.000 1.4744 0.04688 0.04171 -0.0019 0.1846 1.0000
15.250 1.4576 0.05119 0.04603 -0.0022 0.1746 1.0000
15.500 1.4394 0.05582 0.05065 -0.0027 0.1651 1.0000
15.750 1.4239 0.06040 0.05527 -0.0035 0.1563 1.0000
16.000 1.4075 0.06527 0.06015 -0.0045 0.1471 1.0000
16.250 1.3918 0.07012 0.06499 -0.0056 0.1392 1.0000
16.500 1.3779 0.07500 0.06991 -0.0069 0.1308 1.0000
16.750 1.3644 0.07989 0.07484 -0.0082 0.1230 1.0000
17.000 1.3508 0.08485 0.07977 -0.0096 0.1157 1.0000
17.250 1.3393 0.08978 0.08477 -0.0112 0.1081 1.0000
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Polar data table (+)
Polar graphs
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