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 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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