EPPLER 560 AIRFOIL (e560-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 560 AIRFOIL (e560-il) Reynolds number: 500,000 Max Cl/Cd: 105.59 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e560-il-500000.txt Download as CSV file: xf-e560-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 560 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 -0.6343 0.11137 0.10835 -0.0545 1.0000 0.0198
-16.000 -0.6704 0.10088 0.09766 -0.0601 1.0000 0.0194
-15.750 -0.6869 0.09447 0.09114 -0.0635 1.0000 0.0196
-15.500 -0.6999 0.08890 0.08547 -0.0662 1.0000 0.0196
-15.250 -0.7111 0.08388 0.08035 -0.0686 1.0000 0.0196
-15.000 -0.7207 0.07924 0.07562 -0.0707 1.0000 0.0197
-14.750 -0.7290 0.07504 0.07134 -0.0725 1.0000 0.0198
-14.500 -0.7364 0.07115 0.06737 -0.0740 1.0000 0.0199
-14.250 -0.7437 0.06742 0.06357 -0.0753 1.0000 0.0200
-14.000 -0.7503 0.06405 0.06013 -0.0763 1.0000 0.0200
-13.750 -0.7577 0.06085 0.05686 -0.0770 1.0000 0.0201
-13.500 -0.7656 0.05779 0.05375 -0.0775 1.0000 0.0202
-13.250 -0.7736 0.05500 0.05091 -0.0776 1.0000 0.0202
-13.000 -0.7837 0.05221 0.04807 -0.0774 1.0000 0.0203
-12.750 -0.7950 0.04957 0.04539 -0.0768 1.0000 0.0203
-12.500 -0.8103 0.04689 0.04265 -0.0759 1.0000 0.0204
-12.250 -0.8265 0.04430 0.04002 -0.0749 0.9997 0.0205
-12.000 -0.8098 0.04101 0.03664 -0.0807 0.9955 0.0207
-11.750 -0.7961 0.03772 0.03324 -0.0862 0.9897 0.0209
-11.500 -0.7713 0.03432 0.02973 -0.0933 0.9850 0.0210
-11.250 -0.7466 0.03023 0.02550 -0.1015 0.9790 0.0214
-11.000 -0.7135 0.02629 0.02142 -0.1108 0.9742 0.0219
-10.750 -0.6772 0.02408 0.01912 -0.1167 0.9720 0.0224
-10.500 -0.6525 0.02249 0.01745 -0.1187 0.9651 0.0230
-10.250 -0.6171 0.02112 0.01600 -0.1222 0.9622 0.0237
-10.000 -0.5794 0.01997 0.01475 -0.1257 0.9604 0.0246
-9.750 -0.5539 0.01900 0.01369 -0.1263 0.9531 0.0253
-9.500 -0.5186 0.01758 0.01221 -0.1295 0.9500 0.0267
-9.250 -0.4810 0.01662 0.01119 -0.1323 0.9480 0.0282
-9.000 -0.4533 0.01586 0.01034 -0.1328 0.9409 0.0297
-8.750 -0.4183 0.01486 0.00932 -0.1350 0.9372 0.0331
-8.500 -0.3814 0.01389 0.00835 -0.1374 0.9346 0.0410
-8.250 -0.3521 0.01283 0.00741 -0.1385 0.9276 0.0636
-8.000 -0.3169 0.01208 0.00674 -0.1404 0.9225 0.0841
-7.750 -0.2761 0.01151 0.00620 -0.1432 0.9193 0.1004
-7.500 -0.2421 0.01108 0.00577 -0.1445 0.9102 0.1136
-7.250 -0.1972 0.01065 0.00534 -0.1481 0.9049 0.1276
-7.000 -0.1547 0.01031 0.00500 -0.1512 0.8957 0.1413
-6.500 -0.0664 0.00979 0.00442 -0.1580 0.8733 0.1684
-6.250 -0.0299 0.00964 0.00421 -0.1598 0.8579 0.1802
-6.000 0.0034 0.00956 0.00403 -0.1608 0.8413 0.1907
-5.750 0.0339 0.00950 0.00389 -0.1612 0.8248 0.2002
-5.500 0.0629 0.00945 0.00375 -0.1613 0.8085 0.2092
-5.250 0.0911 0.00947 0.00366 -0.1612 0.7926 0.2186
-5.000 0.1185 0.00942 0.00357 -0.1611 0.7772 0.2275
-4.750 0.1460 0.00946 0.00348 -0.1608 0.7627 0.2355
-4.500 0.1731 0.00941 0.00340 -0.1605 0.7486 0.2434
-4.250 0.2003 0.00945 0.00332 -0.1602 0.7349 0.2505
-4.000 0.2272 0.00942 0.00324 -0.1599 0.7213 0.2577
-3.750 0.2543 0.00944 0.00319 -0.1596 0.7085 0.2649
-3.500 0.2814 0.00942 0.00312 -0.1593 0.6961 0.2715
-3.250 0.3083 0.00945 0.00308 -0.1590 0.6839 0.2787
-3.000 0.3354 0.00950 0.00303 -0.1586 0.6718 0.2854
-2.750 0.3625 0.00948 0.00301 -0.1584 0.6604 0.2924
-2.500 0.3896 0.00955 0.00298 -0.1581 0.6494 0.2994
-2.250 0.4166 0.00955 0.00296 -0.1578 0.6382 0.3062
-2.000 0.4437 0.00959 0.00296 -0.1575 0.6273 0.3134
-1.750 0.4708 0.00964 0.00294 -0.1572 0.6173 0.3202
-1.500 0.4979 0.00966 0.00295 -0.1570 0.6069 0.3270
-1.250 0.5251 0.00975 0.00296 -0.1567 0.5971 0.3342
-1.000 0.5519 0.00978 0.00297 -0.1564 0.5872 0.3413
-0.750 0.5792 0.00983 0.00300 -0.1561 0.5778 0.3485
-0.250 0.6333 0.00994 0.00307 -0.1556 0.5599 0.3632
0.000 0.6599 0.01006 0.00310 -0.1552 0.5512 0.3703
0.250 0.6872 0.01007 0.00315 -0.1550 0.5425 0.3780
0.500 0.7138 0.01021 0.00321 -0.1547 0.5347 0.3860
0.750 0.7411 0.01022 0.00327 -0.1545 0.5266 0.3939
1.000 0.7675 0.01036 0.00334 -0.1541 0.5189 0.4021
1.250 0.7947 0.01039 0.00342 -0.1539 0.5112 0.4106
1.500 0.8212 0.01051 0.00350 -0.1535 0.5039 0.4195
1.750 0.8482 0.01058 0.00359 -0.1533 0.4972 0.4281
2.000 0.8747 0.01068 0.00369 -0.1530 0.4900 0.4380
2.250 0.9011 0.01079 0.00380 -0.1526 0.4834 0.4480
2.500 0.9279 0.01086 0.00391 -0.1524 0.4766 0.4586
2.750 0.9540 0.01100 0.00403 -0.1520 0.4705 0.4699
3.000 0.9807 0.01108 0.00417 -0.1517 0.4645 0.4826
3.250 1.0070 0.01118 0.00430 -0.1513 0.4581 0.4963
3.500 1.0327 0.01135 0.00446 -0.1509 0.4522 0.5113
3.750 1.0593 0.01141 0.00461 -0.1506 0.4468 0.5291
4.000 1.0853 0.01150 0.00477 -0.1503 0.4409 0.5501
4.250 1.1106 0.01169 0.00497 -0.1498 0.4353 0.5747
4.500 1.1370 0.01172 0.00515 -0.1495 0.4301 0.6044
4.750 1.1625 0.01181 0.00534 -0.1490 0.4247 0.6423
5.000 1.1870 0.01197 0.00559 -0.1484 0.4193 0.6898
5.250 1.2116 0.01197 0.00581 -0.1477 0.4144 0.7523
5.500 1.2311 0.01192 0.00601 -0.1458 0.4094 0.8473
5.750 1.2478 0.01191 0.00611 -0.1433 0.4045 1.0000
6.000 1.2729 0.01212 0.00632 -0.1428 0.3996 1.0000
6.250 1.2977 0.01229 0.00650 -0.1422 0.3943 1.0000
6.500 1.3209 0.01254 0.00671 -0.1414 0.3891 1.0000
6.750 1.3443 0.01278 0.00695 -0.1405 0.3842 1.0000
7.000 1.3674 0.01295 0.00716 -0.1396 0.3790 1.0000
7.250 1.3893 0.01321 0.00739 -0.1386 0.3737 1.0000
7.500 1.4112 0.01350 0.00767 -0.1375 0.3686 1.0000
7.750 1.4333 0.01368 0.00790 -0.1364 0.3632 1.0000
8.000 1.4539 0.01395 0.00816 -0.1352 0.3576 1.0000
8.250 1.4746 0.01426 0.00847 -0.1339 0.3522 1.0000
8.500 1.4960 0.01447 0.00874 -0.1328 0.3466 1.0000
8.750 1.5154 0.01479 0.00905 -0.1313 0.3410 1.0000
9.000 1.5350 0.01511 0.00939 -0.1299 0.3354 1.0000
9.250 1.5552 0.01538 0.00971 -0.1287 0.3294 1.0000
9.500 1.5724 0.01579 0.01009 -0.1269 0.3233 1.0000
9.750 1.5918 0.01609 0.01045 -0.1256 0.3168 1.0000
10.000 1.6085 0.01649 0.01086 -0.1238 0.3096 1.0000
10.250 1.6256 0.01690 0.01130 -0.1221 0.3025 1.0000
10.500 1.6414 0.01736 0.01177 -0.1203 0.2945 1.0000
10.750 1.6567 0.01785 0.01228 -0.1185 0.2858 1.0000
11.000 1.6694 0.01847 0.01289 -0.1163 0.2769 1.0000
11.250 1.6841 0.01904 0.01349 -0.1145 0.2672 1.0000
11.500 1.6952 0.01979 0.01423 -0.1123 0.2578 1.0000
11.750 1.7057 0.02059 0.01504 -0.1101 0.2472 1.0000
12.000 1.7161 0.02145 0.01591 -0.1079 0.2364 1.0000
12.250 1.7236 0.02251 0.01695 -0.1056 0.2253 1.0000
12.500 1.7286 0.02377 0.01818 -0.1031 0.2137 1.0000
12.750 1.7326 0.02516 0.01956 -0.1007 0.2016 1.0000
13.000 1.7359 0.02668 0.02107 -0.0984 0.1893 1.0000
13.250 1.7370 0.02844 0.02281 -0.0961 0.1772 1.0000
13.500 1.7362 0.03045 0.02481 -0.0940 0.1657 1.0000
13.750 1.7329 0.03278 0.02712 -0.0919 0.1540 1.0000
14.000 1.7283 0.03538 0.02971 -0.0901 0.1434 1.0000
14.250 1.7248 0.03803 0.03235 -0.0885 0.1331 1.0000
14.500 1.7207 0.04088 0.03523 -0.0873 0.1241 1.0000
14.750 1.7141 0.04412 0.03848 -0.0862 0.1165 1.0000
15.000 1.7096 0.04731 0.04171 -0.0855 0.1086 1.0000
15.250 1.7026 0.05089 0.04533 -0.0849 0.1022 1.0000
15.500 1.6959 0.05460 0.04908 -0.0846 0.0955 1.0000
15.750 1.6883 0.05855 0.05308 -0.0845 0.0899 1.0000
16.000 1.6804 0.06266 0.05724 -0.0846 0.0843 1.0000
16.250 1.6715 0.06706 0.06169 -0.0849 0.0795 1.0000
16.500 1.6646 0.07130 0.06600 -0.0854 0.0748 1.0000
17.000 1.6473 0.08057 0.07540 -0.0870 0.0663 1.0000
17.250 1.6373 0.08558 0.08046 -0.0880 0.0623 1.0000
17.500 1.6288 0.09047 0.08541 -0.0892 0.0587 1.0000
17.750 1.6212 0.09527 0.09028 -0.0905 0.0551 1.0000
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Polar data table (+)
Polar graphs
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