EPPLER 560 AIRFOIL (e560-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 560 AIRFOIL (e560-il) Reynolds number: 1,000,000 Max Cl/Cd: 133.1 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e560-il-1000000.txt Download as CSV file: xf-e560-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.500 -0.6583 0.14189 0.13961 -0.0382 1.0000 0.0133
-18.250 -0.6804 0.13343 0.13103 -0.0425 1.0000 0.0133
-18.000 -0.6969 0.12637 0.12387 -0.0460 1.0000 0.0134
-17.750 -0.7075 0.12070 0.11812 -0.0487 1.0000 0.0134
-17.500 -0.7156 0.11565 0.11300 -0.0511 1.0000 0.0134
-17.250 -0.7241 0.11057 0.10785 -0.0535 1.0000 0.0135
-17.000 -0.7301 0.10610 0.10332 -0.0555 1.0000 0.0136
-16.750 -0.7356 0.10182 0.09897 -0.0574 1.0000 0.0135
-16.500 -0.7414 0.09753 0.09463 -0.0592 1.0000 0.0137
-16.250 -0.7465 0.09344 0.09049 -0.0610 1.0000 0.0137
-16.000 -0.7510 0.08964 0.08663 -0.0625 1.0000 0.0137
-15.750 -0.7568 0.08552 0.08245 -0.0643 1.0000 0.0139
-15.500 -0.7607 0.08189 0.07877 -0.0657 1.0000 0.0139
-15.250 -0.7646 0.07839 0.07522 -0.0669 1.0000 0.0139
-15.000 -0.7700 0.07457 0.07135 -0.0685 1.0000 0.0141
-14.750 -0.7754 0.07101 0.06774 -0.0697 1.0000 0.0141
-14.500 -0.7805 0.06772 0.06440 -0.0706 1.0000 0.0141
-14.250 -0.7874 0.06415 0.06077 -0.0718 1.0000 0.0142
-14.000 -0.7943 0.06094 0.05752 -0.0725 1.0000 0.0142
-13.750 -0.8036 0.05772 0.05425 -0.0731 1.0000 0.0143
-13.500 -0.8153 0.05452 0.05101 -0.0733 1.0000 0.0143
-13.250 -0.8157 0.05089 0.04732 -0.0765 0.9989 0.0143
-13.000 -0.8132 0.04620 0.04254 -0.0828 0.9960 0.0144
-12.750 -0.8068 0.04151 0.03776 -0.0899 0.9934 0.0145
-12.500 -0.8133 0.03612 0.03227 -0.0963 0.9865 0.0147
-12.250 -0.7940 0.02997 0.02599 -0.1084 0.9834 0.0150
-12.000 -0.7744 0.02434 0.02018 -0.1190 0.9762 0.0151
-11.750 -0.7419 0.02199 0.01771 -0.1248 0.9739 0.0154
-11.500 -0.7074 0.02040 0.01603 -0.1291 0.9726 0.0157
-11.250 -0.6853 0.01920 0.01475 -0.1298 0.9671 0.0160
-11.000 -0.6543 0.01813 0.01361 -0.1320 0.9640 0.0163
-10.750 -0.6205 0.01716 0.01257 -0.1345 0.9621 0.0167
-10.500 -0.5852 0.01630 0.01164 -0.1370 0.9606 0.0171
-10.250 -0.5631 0.01560 0.01089 -0.1365 0.9537 0.0173
-10.000 -0.5308 0.01489 0.01012 -0.1380 0.9504 0.0176
-9.750 -0.4973 0.01385 0.00900 -0.1401 0.9480 0.0184
-9.500 -0.4735 0.01320 0.00831 -0.1398 0.9400 0.0191
-9.250 -0.4402 0.01258 0.00765 -0.1412 0.9359 0.0199
-9.000 -0.4050 0.01204 0.00705 -0.1430 0.9311 0.0208
-8.750 -0.3688 0.01146 0.00642 -0.1450 0.9242 0.0221
-8.500 -0.3235 0.01085 0.00578 -0.1489 0.9193 0.0247
-8.250 -0.2787 0.01011 0.00508 -0.1530 0.9105 0.0375
-8.000 -0.2269 0.00934 0.00443 -0.1587 0.9008 0.0646
-7.750 -0.1853 0.00894 0.00403 -0.1618 0.8847 0.0810
-7.500 -0.1517 0.00868 0.00374 -0.1632 0.8650 0.0946
-7.250 -0.1223 0.00850 0.00351 -0.1635 0.8450 0.1066
-7.000 -0.0949 0.00836 0.00330 -0.1635 0.8257 0.1187
-6.750 -0.0682 0.00825 0.00314 -0.1632 0.8078 0.1295
-6.500 -0.0417 0.00813 0.00299 -0.1629 0.7910 0.1414
-6.250 -0.0153 0.00804 0.00285 -0.1625 0.7746 0.1514
-6.000 0.0114 0.00798 0.00273 -0.1622 0.7592 0.1602
-5.750 0.0383 0.00792 0.00262 -0.1619 0.7448 0.1703
-5.500 0.0652 0.00786 0.00252 -0.1616 0.7308 0.1795
-5.250 0.0921 0.00785 0.00244 -0.1613 0.7172 0.1875
-4.750 0.1467 0.00778 0.00229 -0.1609 0.6915 0.2046
-4.500 0.1741 0.00775 0.00223 -0.1607 0.6794 0.2139
-4.250 0.2014 0.00775 0.00218 -0.1604 0.6672 0.2223
-4.000 0.2289 0.00774 0.00214 -0.1603 0.6552 0.2306
-3.750 0.2568 0.00775 0.00210 -0.1601 0.6445 0.2370
-3.500 0.2842 0.00774 0.00206 -0.1599 0.6335 0.2442
-3.250 0.3119 0.00778 0.00203 -0.1597 0.6222 0.2504
-3.000 0.3398 0.00777 0.00200 -0.1596 0.6118 0.2572
-2.750 0.3672 0.00780 0.00199 -0.1594 0.6015 0.2638
-2.500 0.3953 0.00782 0.00197 -0.1593 0.5917 0.2699
-2.250 0.4230 0.00784 0.00196 -0.1592 0.5820 0.2769
-2.000 0.4506 0.00789 0.00196 -0.1590 0.5718 0.2831
-1.750 0.4786 0.00790 0.00196 -0.1589 0.5630 0.2900
-1.500 0.5061 0.00795 0.00198 -0.1587 0.5538 0.2969
-1.250 0.5341 0.00799 0.00199 -0.1586 0.5453 0.3031
-0.750 0.5895 0.00808 0.00203 -0.1583 0.5278 0.3165
-0.500 0.6168 0.00814 0.00207 -0.1581 0.5194 0.3236
-0.250 0.6449 0.00818 0.00210 -0.1580 0.5120 0.3304
0.000 0.6721 0.00826 0.00214 -0.1578 0.5037 0.3366
0.250 0.7000 0.00830 0.00219 -0.1577 0.4964 0.3444
0.500 0.7273 0.00839 0.00224 -0.1575 0.4888 0.3509
0.750 0.7548 0.00844 0.00229 -0.1573 0.4821 0.3582
1.000 0.7823 0.00851 0.00235 -0.1572 0.4751 0.3658
1.250 0.8091 0.00861 0.00242 -0.1569 0.4678 0.3729
1.500 0.8370 0.00865 0.00249 -0.1568 0.4617 0.3807
1.750 0.8639 0.00875 0.00257 -0.1565 0.4552 0.3879
2.000 0.8910 0.00882 0.00265 -0.1563 0.4493 0.3968
2.250 0.9183 0.00890 0.00273 -0.1561 0.4432 0.4043
2.500 0.9447 0.00901 0.00283 -0.1557 0.4366 0.4134
2.750 0.9720 0.00908 0.00292 -0.1555 0.4315 0.4226
3.000 0.9990 0.00915 0.00302 -0.1553 0.4259 0.4329
3.250 1.0249 0.00928 0.00314 -0.1549 0.4198 0.4426
3.500 1.0521 0.00935 0.00324 -0.1547 0.4150 0.4544
3.750 1.0788 0.00943 0.00336 -0.1544 0.4098 0.4674
4.000 1.1045 0.00956 0.00350 -0.1540 0.4041 0.4811
4.250 1.1312 0.00964 0.00362 -0.1537 0.3994 0.4964
4.500 1.1577 0.00972 0.00375 -0.1534 0.3945 0.5150
4.750 1.1831 0.00985 0.00391 -0.1529 0.3891 0.5362
5.250 1.2353 0.01002 0.00422 -0.1522 0.3796 0.5889
5.500 1.2606 0.01013 0.00441 -0.1517 0.3743 0.6245
5.750 1.2854 0.01024 0.00461 -0.1512 0.3692 0.6671
6.000 1.3113 0.01027 0.00479 -0.1508 0.3647 0.7200
6.250 1.3349 0.01031 0.00500 -0.1499 0.3596 0.7933
6.500 1.3471 0.01019 0.00517 -0.1465 0.3544 1.0000
6.750 1.3723 0.01031 0.00531 -0.1460 0.3501 1.0000
7.000 1.3961 0.01049 0.00548 -0.1452 0.3447 1.0000
7.250 1.4179 0.01075 0.00570 -0.1440 0.3387 1.0000
7.500 1.4421 0.01090 0.00588 -0.1434 0.3340 1.0000
7.750 1.4650 0.01110 0.00607 -0.1424 0.3286 1.0000
8.000 1.4857 0.01139 0.00633 -0.1411 0.3224 1.0000
8.250 1.5096 0.01155 0.00652 -0.1404 0.3177 1.0000
8.500 1.5314 0.01179 0.00676 -0.1393 0.3114 1.0000
8.750 1.5522 0.01208 0.00702 -0.1381 0.3046 1.0000
9.000 1.5734 0.01233 0.00728 -0.1370 0.2966 1.0000
9.250 1.5928 0.01266 0.00758 -0.1355 0.2885 1.0000
9.500 1.6126 0.01299 0.00788 -0.1342 0.2797 1.0000
9.750 1.6316 0.01334 0.00822 -0.1327 0.2704 1.0000
10.000 1.6481 0.01380 0.00864 -0.1309 0.2602 1.0000
10.250 1.6661 0.01419 0.00901 -0.1293 0.2503 1.0000
10.500 1.6824 0.01467 0.00946 -0.1275 0.2403 1.0000
10.750 1.6965 0.01524 0.00999 -0.1254 0.2292 1.0000
11.000 1.7097 0.01586 0.01057 -0.1231 0.2168 1.0000
11.250 1.7221 0.01653 0.01120 -0.1209 0.2044 1.0000
11.500 1.7315 0.01735 0.01196 -0.1183 0.1903 1.0000
11.750 1.7378 0.01836 0.01288 -0.1153 0.1748 1.0000
12.000 1.7443 0.01938 0.01385 -0.1125 0.1616 1.0000
12.250 1.7504 0.02047 0.01490 -0.1098 0.1498 1.0000
12.500 1.7542 0.02173 0.01612 -0.1070 0.1377 1.0000
12.750 1.7567 0.02315 0.01749 -0.1042 0.1261 1.0000
13.000 1.7578 0.02473 0.01904 -0.1015 0.1152 1.0000
13.250 1.7582 0.02646 0.02074 -0.0989 0.1054 1.0000
13.500 1.7609 0.02812 0.02240 -0.0968 0.0975 1.0000
13.750 1.7609 0.03009 0.02436 -0.0947 0.0899 1.0000
14.000 1.7604 0.03221 0.02649 -0.0929 0.0829 1.0000
14.250 1.7609 0.03437 0.02867 -0.0913 0.0769 1.0000
14.500 1.7575 0.03699 0.03130 -0.0897 0.0707 1.0000
14.750 1.7577 0.03940 0.03375 -0.0886 0.0659 1.0000
15.000 1.7525 0.04248 0.03684 -0.0875 0.0605 1.0000
15.250 1.7508 0.04533 0.03974 -0.0867 0.0562 1.0000
15.750 1.7411 0.05207 0.04656 -0.0856 0.0481 1.0000
16.000 1.7334 0.05598 0.05051 -0.0855 0.0444 1.0000
16.250 1.7282 0.05971 0.05430 -0.0855 0.0411 1.0000
16.500 1.7202 0.06392 0.05856 -0.0857 0.0379 1.0000
16.750 1.7129 0.06817 0.06287 -0.0861 0.0348 1.0000
17.000 1.7042 0.07274 0.06750 -0.0867 0.0320 1.0000
17.250 1.6949 0.07749 0.07232 -0.0875 0.0291 1.0000
17.500 1.6836 0.08266 0.07754 -0.0886 0.0260 1.0000
17.750 1.6744 0.08764 0.08258 -0.0898 0.0233 1.0000
18.000 1.6619 0.09321 0.08820 -0.0912 0.0200 1.0000
18.250 1.6491 0.09892 0.09397 -0.0929 0.0170 1.0000
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