EPPLER 561 AIRFOIL (e561-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 561 AIRFOIL (e561-il) Reynolds number: 200,000 Max Cl/Cd: 74.1 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e561-il-200000-n5.txt Download as CSV file: xf-e561-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 561 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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.5319 0.10163 0.09711 -0.0611 1.0000 0.0196
-14.500 -0.5514 0.09455 0.08991 -0.0645 1.0000 0.0196
-14.250 -0.5649 0.08895 0.08420 -0.0670 1.0000 0.0196
-14.000 -0.5752 0.08412 0.07929 -0.0690 1.0000 0.0197
-13.750 -0.5841 0.07974 0.07484 -0.0707 1.0000 0.0198
-13.500 -0.5917 0.07582 0.07085 -0.0720 1.0000 0.0198
-13.250 -0.5986 0.07220 0.06717 -0.0731 1.0000 0.0199
-13.000 -0.6058 0.06881 0.06373 -0.0739 1.0000 0.0200
-12.750 -0.6139 0.06561 0.06050 -0.0744 1.0000 0.0201
-12.500 -0.6230 0.06255 0.05739 -0.0746 1.0000 0.0203
-12.250 -0.6326 0.05971 0.05452 -0.0745 1.0000 0.0203
-12.000 -0.6451 0.05686 0.05165 -0.0741 1.0000 0.0205
-11.750 -0.6315 0.05320 0.04789 -0.0794 0.9959 0.0207
-11.500 -0.6184 0.04969 0.04428 -0.0844 0.9907 0.0210
-11.250 -0.6053 0.04619 0.04067 -0.0895 0.9844 0.0214
-11.000 -0.5959 0.04289 0.03729 -0.0936 0.9753 0.0215
-10.750 -0.5911 0.03954 0.03385 -0.0971 0.9630 0.0218
-10.500 -0.5849 0.03576 0.02999 -0.1017 0.9490 0.0221
-10.250 -0.5693 0.03162 0.02572 -0.1085 0.9358 0.0225
-10.000 -0.5478 0.02869 0.02264 -0.1136 0.9244 0.0231
-9.750 -0.5176 0.02658 0.02038 -0.1180 0.9176 0.0242
-9.500 -0.4919 0.02502 0.01867 -0.1202 0.9065 0.0253
-9.250 -0.4592 0.02337 0.01691 -0.1237 0.8988 0.0267
-9.000 -0.4256 0.02203 0.01544 -0.1267 0.8895 0.0283
-8.750 -0.3876 0.02077 0.01404 -0.1302 0.8809 0.0306
-8.500 -0.3468 0.01958 0.01272 -0.1341 0.8714 0.0345
-8.250 -0.3075 0.01845 0.01152 -0.1376 0.8604 0.0415
-8.000 -0.2665 0.01736 0.01039 -0.1414 0.8491 0.0559
-7.750 -0.2291 0.01648 0.00951 -0.1442 0.8355 0.0759
-7.500 -0.1948 0.01585 0.00885 -0.1461 0.8213 0.0948
-7.250 -0.1618 0.01538 0.00831 -0.1476 0.8070 0.1116
-7.000 -0.1302 0.01503 0.00788 -0.1486 0.7928 0.1266
-6.750 -0.0998 0.01474 0.00751 -0.1493 0.7790 0.1445
-6.500 -0.0709 0.01450 0.00723 -0.1497 0.7651 0.1623
-6.250 -0.0427 0.01433 0.00700 -0.1499 0.7517 0.1776
-6.000 -0.0143 0.01422 0.00676 -0.1500 0.7391 0.1905
-5.750 0.0139 0.01411 0.00656 -0.1501 0.7268 0.2012
-5.500 0.0413 0.01400 0.00637 -0.1500 0.7143 0.2104
-5.250 0.0690 0.01393 0.00617 -0.1499 0.7030 0.2200
-4.750 0.1239 0.01380 0.00583 -0.1496 0.6808 0.2368
-4.500 0.1513 0.01373 0.00571 -0.1495 0.6703 0.2445
-4.250 0.1787 0.01370 0.00555 -0.1493 0.6598 0.2528
-4.000 0.2061 0.01365 0.00545 -0.1491 0.6502 0.2601
-3.750 0.2335 0.01364 0.00533 -0.1490 0.6407 0.2682
-3.500 0.2608 0.01361 0.00524 -0.1488 0.6312 0.2758
-3.250 0.2881 0.01362 0.00516 -0.1486 0.6221 0.2837
-3.000 0.3155 0.01360 0.00507 -0.1484 0.6129 0.2913
-2.750 0.3428 0.01362 0.00503 -0.1482 0.6048 0.2989
-2.500 0.3703 0.01363 0.00496 -0.1480 0.5965 0.3069
-2.250 0.3974 0.01364 0.00494 -0.1478 0.5883 0.3139
-2.000 0.4248 0.01367 0.00490 -0.1476 0.5804 0.3222
-1.750 0.4519 0.01370 0.00489 -0.1474 0.5725 0.3292
-1.500 0.4792 0.01375 0.00489 -0.1472 0.5656 0.3371
-1.250 0.5065 0.01379 0.00488 -0.1470 0.5582 0.3448
-1.000 0.5336 0.01386 0.00490 -0.1468 0.5516 0.3525
-0.750 0.5609 0.01391 0.00491 -0.1466 0.5444 0.3605
-0.500 0.5878 0.01396 0.00495 -0.1464 0.5377 0.3680
-0.250 0.6150 0.01405 0.00498 -0.1462 0.5318 0.3765
0.000 0.6421 0.01410 0.00505 -0.1460 0.5254 0.3840
0.250 0.6690 0.01419 0.00510 -0.1457 0.5194 0.3926
0.500 0.6959 0.01428 0.00517 -0.1455 0.5136 0.4007
0.750 0.7228 0.01435 0.00526 -0.1453 0.5076 0.4092
1.000 0.7495 0.01446 0.00534 -0.1450 0.5023 0.4180
1.250 0.7763 0.01457 0.00545 -0.1448 0.4974 0.4271
1.500 0.8031 0.01465 0.00556 -0.1446 0.4916 0.4361
1.750 0.8294 0.01476 0.00568 -0.1443 0.4863 0.4458
2.000 0.8560 0.01491 0.00579 -0.1440 0.4818 0.4559
2.250 0.8825 0.01500 0.00595 -0.1437 0.4768 0.4667
2.500 0.9088 0.01511 0.00611 -0.1434 0.4717 0.4776
2.750 0.9349 0.01526 0.00625 -0.1431 0.4671 0.4900
3.000 0.9610 0.01540 0.00643 -0.1428 0.4627 0.5032
3.250 0.9870 0.01551 0.00663 -0.1424 0.4580 0.5175
3.500 1.0126 0.01565 0.00682 -0.1420 0.4534 0.5334
3.750 1.0380 0.01581 0.00701 -0.1416 0.4492 0.5512
4.000 1.0635 0.01595 0.00724 -0.1411 0.4449 0.5718
4.250 1.0886 0.01608 0.00749 -0.1407 0.4404 0.5956
4.500 1.1133 0.01622 0.00772 -0.1401 0.4361 0.6230
4.750 1.1376 0.01638 0.00795 -0.1394 0.4322 0.6565
5.000 1.1612 0.01651 0.00823 -0.1386 0.4281 0.6983
5.250 1.1832 0.01659 0.00851 -0.1374 0.4238 0.7515
5.500 1.2006 0.01661 0.00872 -0.1351 0.4197 0.8330
5.750 1.2201 0.01663 0.00882 -0.1333 0.4160 1.0000
6.000 1.2450 0.01691 0.00910 -0.1329 0.4121 1.0000
6.250 1.2689 0.01718 0.00941 -0.1323 0.4077 1.0000
6.500 1.2925 0.01746 0.00970 -0.1317 0.4033 1.0000
6.750 1.3160 0.01776 0.00998 -0.1310 0.3994 1.0000
7.000 1.3394 0.01808 0.01029 -0.1304 0.3956 1.0000
7.250 1.3613 0.01838 0.01066 -0.1294 0.3911 1.0000
7.500 1.3826 0.01868 0.01100 -0.1284 0.3867 1.0000
7.750 1.4037 0.01901 0.01131 -0.1273 0.3828 1.0000
8.000 1.4242 0.01935 0.01168 -0.1262 0.3788 1.0000
8.250 1.4430 0.01969 0.01211 -0.1248 0.3742 1.0000
8.500 1.4619 0.02005 0.01251 -0.1234 0.3697 1.0000
8.750 1.4809 0.02043 0.01288 -0.1220 0.3656 1.0000
9.000 1.4988 0.02084 0.01336 -0.1205 0.3612 1.0000
9.250 1.5157 0.02125 0.01386 -0.1189 0.3563 1.0000
9.500 1.5321 0.02169 0.01433 -0.1172 0.3516 1.0000
9.750 1.5486 0.02217 0.01480 -0.1156 0.3472 1.0000
10.000 1.5630 0.02267 0.01544 -0.1137 0.3418 1.0000
10.250 1.5769 0.02320 0.01603 -0.1118 0.3364 1.0000
10.500 1.5904 0.02379 0.01661 -0.1099 0.3315 1.0000
10.750 1.6026 0.02443 0.01738 -0.1079 0.3256 1.0000
11.000 1.6136 0.02513 0.01814 -0.1058 0.3198 1.0000
11.250 1.6243 0.02590 0.01894 -0.1038 0.3144 1.0000
11.500 1.6341 0.02675 0.01990 -0.1018 0.3081 1.0000
11.750 1.6423 0.02770 0.02088 -0.0997 0.3022 1.0000
12.000 1.6507 0.02872 0.02200 -0.0978 0.2962 1.0000
12.250 1.6574 0.02988 0.02324 -0.0959 0.2896 1.0000
12.500 1.6628 0.03117 0.02456 -0.0940 0.2835 1.0000
12.750 1.6679 0.03258 0.02608 -0.0922 0.2764 1.0000
13.000 1.6701 0.03423 0.02773 -0.0903 0.2697 1.0000
13.250 1.6736 0.03592 0.02955 -0.0888 0.2622 1.0000
13.500 1.6733 0.03796 0.03160 -0.0872 0.2550 1.0000
13.750 1.6745 0.04003 0.03378 -0.0859 0.2474 1.0000
14.000 1.6714 0.04253 0.03631 -0.0846 0.2398 1.0000
14.250 1.6700 0.04505 0.03892 -0.0836 0.2315 1.0000
14.500 1.6639 0.04810 0.04200 -0.0827 0.2235 1.0000
14.750 1.6599 0.05114 0.04512 -0.0821 0.2149 1.0000
15.000 1.6524 0.05465 0.04867 -0.0816 0.2066 1.0000
15.250 1.6449 0.05832 0.05240 -0.0813 0.1980 1.0000
15.500 1.6369 0.06220 0.05633 -0.0813 0.1897 1.0000
15.750 1.6257 0.06659 0.06075 -0.0814 0.1813 1.0000
16.000 1.6174 0.07080 0.06504 -0.0818 0.1726 1.0000
16.250 1.6059 0.07551 0.06977 -0.0824 0.1648 1.0000
16.500 1.5958 0.08019 0.07451 -0.0831 0.1563 1.0000
16.750 1.5853 0.08502 0.07939 -0.0840 0.1486 1.0000
17.000 1.5734 0.09015 0.08455 -0.0852 0.1408 1.0000
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Polar data table (+)
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