EPPLER 561 AIRFOIL (e561-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 561 AIRFOIL (e561-il) Reynolds number: 500,000 Max Cl/Cd: 105.02 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e561-il-500000.txt Download as CSV file: xf-e561-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.5640 0.11659 0.11364 -0.0544 1.0000 0.0186
-16.000 -0.5913 0.10719 0.10409 -0.0596 1.0000 0.0184
-15.750 -0.6188 0.09846 0.09521 -0.0643 1.0000 0.0183
-15.500 -0.6373 0.09170 0.08834 -0.0679 1.0000 0.0183
-15.250 -0.6502 0.08635 0.08290 -0.0704 1.0000 0.0181
-15.000 -0.6670 0.08041 0.07684 -0.0735 1.0000 0.0181
-14.750 -0.6776 0.07577 0.07211 -0.0757 1.0000 0.0181
-14.500 -0.6895 0.07106 0.06729 -0.0781 1.0000 0.0181
-14.250 -0.6996 0.06699 0.06313 -0.0797 1.0000 0.0181
-14.000 -0.7086 0.06337 0.05943 -0.0809 1.0000 0.0181
-13.750 -0.7185 0.05987 0.05585 -0.0819 1.0000 0.0181
-13.500 -0.7270 0.05677 0.05268 -0.0825 1.0000 0.0181
-13.250 -0.7382 0.05353 0.04936 -0.0831 1.0000 0.0182
-13.000 -0.7467 0.05100 0.04679 -0.0827 1.0000 0.0182
-12.750 -0.7590 0.04835 0.04409 -0.0822 1.0000 0.0183
-12.500 -0.7619 0.04541 0.04106 -0.0839 0.9989 0.0183
-12.250 -0.7424 0.04224 0.03778 -0.0896 0.9953 0.0184
-12.000 -0.7250 0.03930 0.03475 -0.0941 0.9913 0.0186
-11.750 -0.7071 0.03662 0.03202 -0.0982 0.9860 0.0188
-11.500 -0.6888 0.03381 0.02916 -0.1029 0.9803 0.0190
-11.250 -0.6647 0.03064 0.02592 -0.1091 0.9737 0.0193
-11.000 -0.6388 0.02749 0.02268 -0.1156 0.9660 0.0196
-10.750 -0.6063 0.02513 0.02022 -0.1213 0.9612 0.0200
-10.500 -0.5818 0.02347 0.01847 -0.1236 0.9531 0.0205
-10.250 -0.5487 0.02202 0.01694 -0.1268 0.9485 0.0211
-10.000 -0.5222 0.02080 0.01563 -0.1282 0.9405 0.0215
-9.750 -0.4904 0.01954 0.01428 -0.1305 0.9350 0.0220
-9.500 -0.4619 0.01801 0.01269 -0.1325 0.9267 0.0227
-9.250 -0.4256 0.01686 0.01147 -0.1354 0.9206 0.0235
-9.000 -0.3867 0.01592 0.01046 -0.1385 0.9136 0.0245
-8.750 -0.3428 0.01509 0.00952 -0.1424 0.9057 0.0257
-8.500 -0.2954 0.01406 0.00842 -0.1474 0.8967 0.0279
-8.250 -0.2488 0.01329 0.00753 -0.1518 0.8847 0.0315
-7.750 -0.1800 0.01152 0.00585 -0.1561 0.8499 0.0781
-7.500 -0.1508 0.01109 0.00542 -0.1567 0.8319 0.1020
-7.250 -0.1228 0.01082 0.00511 -0.1569 0.8146 0.1190
-6.750 -0.0685 0.01047 0.00465 -0.1567 0.7829 0.1464
-6.500 -0.0416 0.01037 0.00447 -0.1565 0.7682 0.1584
-6.250 -0.0148 0.01025 0.00431 -0.1563 0.7538 0.1714
-6.000 0.0121 0.01016 0.00417 -0.1560 0.7404 0.1834
-5.500 0.0663 0.01007 0.00394 -0.1556 0.7150 0.2041
-5.250 0.0934 0.01001 0.00383 -0.1553 0.7031 0.2135
-5.000 0.1206 0.01003 0.00374 -0.1551 0.6914 0.2229
-4.750 0.1478 0.00998 0.00368 -0.1549 0.6795 0.2338
-4.500 0.1751 0.00996 0.00360 -0.1547 0.6687 0.2432
-4.250 0.2024 0.00997 0.00354 -0.1544 0.6582 0.2514
-4.000 0.2300 0.00993 0.00345 -0.1543 0.6479 0.2590
-3.750 0.2572 0.00995 0.00340 -0.1540 0.6380 0.2667
-3.500 0.2848 0.00994 0.00333 -0.1538 0.6278 0.2741
-3.250 0.3122 0.00994 0.00330 -0.1536 0.6186 0.2818
-3.000 0.3399 0.00998 0.00326 -0.1535 0.6093 0.2891
-2.750 0.3673 0.00997 0.00323 -0.1533 0.6009 0.2971
-2.500 0.3949 0.01000 0.00321 -0.1531 0.5919 0.3048
-2.250 0.4224 0.01002 0.00319 -0.1529 0.5837 0.3123
-2.000 0.4500 0.01005 0.00319 -0.1528 0.5751 0.3201
-1.750 0.4774 0.01011 0.00318 -0.1526 0.5677 0.3277
-1.500 0.5052 0.01011 0.00320 -0.1525 0.5600 0.3352
-1.250 0.5324 0.01022 0.00321 -0.1522 0.5525 0.3426
-1.000 0.5601 0.01021 0.00324 -0.1521 0.5453 0.3506
-0.750 0.5875 0.01029 0.00326 -0.1519 0.5381 0.3582
-0.500 0.6149 0.01034 0.00330 -0.1517 0.5318 0.3657
-0.250 0.6426 0.01039 0.00334 -0.1516 0.5253 0.3740
0.000 0.6696 0.01047 0.00338 -0.1514 0.5189 0.3816
0.250 0.6971 0.01053 0.00344 -0.1512 0.5129 0.3894
0.500 0.7246 0.01060 0.00349 -0.1511 0.5068 0.3976
0.750 0.7515 0.01068 0.00356 -0.1508 0.5012 0.4059
1.000 0.7790 0.01077 0.00364 -0.1507 0.4959 0.4142
1.250 0.8063 0.01080 0.00372 -0.1505 0.4903 0.4229
1.500 0.8331 0.01093 0.00379 -0.1502 0.4849 0.4322
1.750 0.8602 0.01102 0.00390 -0.1501 0.4801 0.4410
2.000 0.8875 0.01108 0.00399 -0.1499 0.4753 0.4511
2.250 0.9143 0.01116 0.00409 -0.1497 0.4702 0.4613
2.500 0.9408 0.01133 0.00422 -0.1494 0.4653 0.4721
2.750 0.9679 0.01137 0.00434 -0.1492 0.4611 0.4841
3.000 0.9947 0.01144 0.00446 -0.1490 0.4565 0.4971
3.250 1.0210 0.01155 0.00459 -0.1487 0.4519 0.5112
3.500 1.0475 0.01172 0.00476 -0.1485 0.4474 0.5272
3.750 1.0741 0.01176 0.00491 -0.1482 0.4435 0.5464
4.000 1.1004 0.01183 0.00507 -0.1479 0.4392 0.5686
4.250 1.1263 0.01195 0.00523 -0.1476 0.4349 0.5953
4.500 1.1524 0.01212 0.00545 -0.1473 0.4305 0.6285
4.750 1.1781 0.01213 0.00565 -0.1469 0.4269 0.6701
5.000 1.2030 0.01216 0.00585 -0.1463 0.4227 0.7229
5.250 1.2256 0.01218 0.00606 -0.1452 0.4186 0.7959
5.500 1.2399 0.01206 0.00617 -0.1421 0.4149 1.0000
5.750 1.2656 0.01223 0.00636 -0.1417 0.4112 1.0000
6.000 1.2907 0.01238 0.00654 -0.1413 0.4071 1.0000
6.250 1.3154 0.01258 0.00672 -0.1407 0.4031 1.0000
6.500 1.3397 0.01285 0.00694 -0.1402 0.3989 1.0000
6.750 1.3640 0.01306 0.00717 -0.1396 0.3950 1.0000
7.000 1.3871 0.01322 0.00737 -0.1387 0.3910 1.0000
7.250 1.4093 0.01342 0.00758 -0.1377 0.3869 1.0000
7.500 1.4314 0.01369 0.00781 -0.1367 0.3827 1.0000
7.750 1.4536 0.01395 0.00809 -0.1358 0.3787 1.0000
8.000 1.4747 0.01413 0.00833 -0.1346 0.3745 1.0000
8.250 1.4954 0.01436 0.00858 -0.1334 0.3702 1.0000
8.500 1.5156 0.01469 0.00887 -0.1321 0.3656 1.0000
8.750 1.5360 0.01494 0.00917 -0.1309 0.3613 1.0000
9.000 1.5556 0.01517 0.00946 -0.1295 0.3565 1.0000
9.250 1.5740 0.01548 0.00976 -0.1280 0.3515 1.0000
9.500 1.5923 0.01584 0.01013 -0.1265 0.3466 1.0000
9.750 1.6112 0.01610 0.01047 -0.1250 0.3415 1.0000
10.000 1.6283 0.01646 0.01084 -0.1234 0.3363 1.0000
10.250 1.6442 0.01692 0.01129 -0.1216 0.3311 1.0000
10.500 1.6621 0.01724 0.01171 -0.1202 0.3257 1.0000
10.750 1.6770 0.01771 0.01218 -0.1183 0.3197 1.0000
11.000 1.6911 0.01823 0.01273 -0.1164 0.3139 1.0000
11.250 1.7059 0.01872 0.01326 -0.1146 0.3067 1.0000
11.500 1.7162 0.01944 0.01397 -0.1123 0.2997 1.0000
11.750 1.7299 0.02002 0.01462 -0.1106 0.2916 1.0000
12.000 1.7382 0.02090 0.01549 -0.1082 0.2838 1.0000
12.250 1.7501 0.02167 0.01630 -0.1064 0.2755 1.0000
12.500 1.7570 0.02273 0.01736 -0.1042 0.2675 1.0000
12.750 1.7661 0.02374 0.01841 -0.1023 0.2591 1.0000
13.000 1.7719 0.02500 0.01968 -0.1002 0.2513 1.0000
13.250 1.7773 0.02636 0.02107 -0.0982 0.2426 1.0000
13.500 1.7817 0.02785 0.02259 -0.0963 0.2343 1.0000
13.750 1.7819 0.02974 0.02447 -0.0943 0.2254 1.0000
14.000 1.7852 0.03150 0.02627 -0.0927 0.2165 1.0000
14.250 1.7824 0.03384 0.02863 -0.0910 0.2073 1.0000
14.500 1.7792 0.03636 0.03116 -0.0895 0.1973 1.0000
14.750 1.7763 0.03898 0.03380 -0.0882 0.1879 1.0000
15.000 1.7687 0.04217 0.03699 -0.0870 0.1793 1.0000
15.250 1.7617 0.04547 0.04032 -0.0860 0.1695 1.0000
15.500 1.7539 0.04899 0.04387 -0.0853 0.1606 1.0000
15.750 1.7413 0.05319 0.04808 -0.0848 0.1521 1.0000
16.000 1.7324 0.05714 0.05206 -0.0846 0.1433 1.0000
16.250 1.7209 0.06154 0.05650 -0.0846 0.1359 1.0000
16.500 1.7091 0.06611 0.06111 -0.0848 0.1284 1.0000
16.750 1.6992 0.07058 0.06562 -0.0852 0.1219 1.0000
17.000 1.6866 0.07554 0.07061 -0.0858 0.1153 1.0000
17.250 1.6772 0.08016 0.07530 -0.0865 0.1094 1.0000
17.500 1.6648 0.08532 0.08049 -0.0875 0.1034 1.0000
17.750 1.6555 0.09013 0.08536 -0.0885 0.0981 1.0000
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Polar data table (+)
Polar graphs
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