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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.750 -0.5819 0.13682 0.13368 -0.0438 1.0000 0.0117 -17.500 -0.5988 0.12945 0.12620 -0.0473 1.0000 0.0117 -17.250 -0.6086 0.12376 0.12042 -0.0499 1.0000 0.0117 -17.000 -0.6181 0.11828 0.11486 -0.0524 1.0000 0.0118 -16.750 -0.6247 0.11349 0.11000 -0.0545 1.0000 0.0118 -16.500 -0.6312 0.10878 0.10522 -0.0566 1.0000 0.0119 -16.250 -0.6373 0.10426 0.10063 -0.0586 1.0000 0.0119 -16.000 -0.6420 0.10009 0.09640 -0.0603 1.0000 0.0120 -15.750 -0.6485 0.09564 0.09188 -0.0622 1.0000 0.0121 -15.500 -0.6518 0.09190 0.08809 -0.0636 1.0000 0.0121 -15.250 -0.6551 0.08831 0.08446 -0.0650 1.0000 0.0121 -15.000 -0.6605 0.08436 0.08044 -0.0665 1.0000 0.0122 -14.750 -0.6639 0.08093 0.07698 -0.0676 1.0000 0.0122 -14.500 -0.6689 0.07727 0.07326 -0.0689 1.0000 0.0123 -14.250 -0.6741 0.07377 0.06971 -0.0700 1.0000 0.0123 -14.000 -0.6791 0.07044 0.06635 -0.0709 1.0000 0.0123 -13.750 -0.6859 0.06694 0.06279 -0.0719 1.0000 0.0124 -13.500 -0.6782 0.06300 0.05878 -0.0763 0.9985 0.0124 -13.250 -0.6735 0.05876 0.05450 -0.0810 0.9963 0.0126 -13.000 -0.6676 0.05464 0.05031 -0.0860 0.9940 0.0127 -12.750 -0.6661 0.05029 0.04590 -0.0907 0.9907 0.0128 -12.500 -0.6630 0.04598 0.04153 -0.0958 0.9866 0.0130 -12.250 -0.6542 0.04174 0.03720 -0.1018 0.9830 0.0131 -12.000 -0.6582 0.03776 0.03315 -0.1050 0.9741 0.0132 -11.750 -0.6656 0.03377 0.02908 -0.1078 0.9610 0.0133 -11.500 -0.6655 0.02953 0.02472 -0.1120 0.9447 0.0133 -11.250 -0.6443 0.02525 0.02028 -0.1202 0.9335 0.0136 -11.000 -0.6178 0.02306 0.01794 -0.1245 0.9232 0.0138 -10.750 -0.5821 0.02136 0.01612 -0.1291 0.9161 0.0141 -10.500 -0.5427 0.01996 0.01460 -0.1336 0.9068 0.0145 -10.250 -0.4933 0.01870 0.01320 -0.1398 0.8979 0.0149 -10.000 -0.4400 0.01764 0.01198 -0.1464 0.8858 0.0153 -9.750 -0.3976 0.01658 0.01077 -0.1509 0.8668 0.0159 -9.500 -0.3649 0.01591 0.00995 -0.1529 0.8454 0.0165 -9.250 -0.3373 0.01540 0.00928 -0.1535 0.8248 0.0171 -9.000 -0.3118 0.01498 0.00871 -0.1536 0.8058 0.0177 -8.750 -0.2869 0.01461 0.00820 -0.1534 0.7884 0.0184 -8.500 -0.2624 0.01419 0.00766 -0.1532 0.7722 0.0195 -8.250 -0.2377 0.01383 0.00719 -0.1529 0.7569 0.0212 -8.000 -0.2129 0.01345 0.00672 -0.1527 0.7428 0.0241 -7.750 -0.1879 0.01304 0.00626 -0.1525 0.7292 0.0303 -7.500 -0.1626 0.01259 0.00580 -0.1524 0.7161 0.0423 -7.250 -0.1370 0.01220 0.00539 -0.1523 0.7036 0.0557 -7.000 -0.1112 0.01187 0.00504 -0.1521 0.6917 0.0697 -6.750 -0.0846 0.01156 0.00473 -0.1521 0.6804 0.0839 -6.500 -0.0579 0.01130 0.00446 -0.1520 0.6697 0.0980 -6.250 -0.0313 0.01108 0.00423 -0.1519 0.6582 0.1140 -6.000 -0.0041 0.01087 0.00402 -0.1519 0.6475 0.1306 -5.750 0.0229 0.01071 0.00385 -0.1518 0.6376 0.1458 -5.500 0.0506 0.01059 0.00370 -0.1517 0.6281 0.1580 -5.250 0.0779 0.01048 0.00356 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0.4805 0.3214 -0.250 0.6323 0.01047 0.00295 -0.1495 0.4754 0.3286 0.000 0.6596 0.01053 0.00300 -0.1493 0.4699 0.3359 0.500 0.7143 0.01065 0.00311 -0.1489 0.4599 0.3501 0.750 0.7416 0.01072 0.00317 -0.1488 0.4549 0.3576 1.000 0.7684 0.01081 0.00324 -0.1485 0.4503 0.3642 1.250 0.7955 0.01089 0.00333 -0.1483 0.4459 0.3721 1.500 0.8228 0.01096 0.00340 -0.1481 0.4412 0.3794 1.750 0.8496 0.01104 0.00349 -0.1479 0.4366 0.3869 2.000 0.8760 0.01115 0.00359 -0.1476 0.4325 0.3949 2.250 0.9029 0.01123 0.00370 -0.1473 0.4286 0.4028 2.500 0.9299 0.01131 0.00380 -0.1471 0.4243 0.4112 2.750 0.9563 0.01141 0.00392 -0.1468 0.4199 0.4193 3.000 0.9822 0.01153 0.00404 -0.1464 0.4160 0.4290 3.250 1.0084 0.01164 0.00417 -0.1461 0.4124 0.4380 3.500 1.0350 0.01173 0.00431 -0.1458 0.4085 0.4481 3.750 1.0611 0.01183 0.00445 -0.1455 0.4044 0.4593 4.250 1.1115 0.01211 0.00477 -0.1445 0.3968 0.4837 4.500 1.1378 0.01219 0.00492 -0.1442 0.3932 0.4982 4.750 1.1633 0.01230 0.00509 -0.1438 0.3893 0.5145 5.000 1.1882 0.01244 0.00528 -0.1432 0.3853 0.5322 5.250 1.2120 0.01260 0.00548 -0.1425 0.3814 0.5532 5.500 1.2370 0.01270 0.00568 -0.1420 0.3781 0.5777 5.750 1.2615 0.01280 0.00588 -0.1414 0.3743 0.6055 6.000 1.2848 0.01291 0.00610 -0.1406 0.3702 0.6390 6.250 1.3069 0.01305 0.00634 -0.1396 0.3663 0.6807 6.500 1.3292 0.01316 0.00660 -0.1386 0.3628 0.7319 6.750 1.3503 0.01319 0.00685 -0.1372 0.3590 0.8045 7.000 1.3640 0.01309 0.00700 -0.1342 0.3551 1.0000 7.250 1.3856 0.01334 0.00724 -0.1332 0.3509 1.0000 7.500 1.4072 0.01361 0.00750 -0.1321 0.3470 1.0000 7.750 1.4300 0.01382 0.00775 -0.1313 0.3429 1.0000 8.000 1.4514 0.01408 0.00803 -0.1302 0.3383 1.0000 8.250 1.4710 0.01440 0.00833 -0.1289 0.3337 1.0000 8.500 1.4919 0.01468 0.00863 -0.1278 0.3294 1.0000 8.750 1.5127 0.01496 0.00895 -0.1267 0.3242 1.0000 9.000 1.5309 0.01532 0.00931 -0.1252 0.3187 1.0000 9.250 1.5497 0.01568 0.00968 -0.1238 0.3135 1.0000 9.500 1.5686 0.01604 0.01006 -0.1225 0.3073 1.0000 9.750 1.5841 0.01652 0.01054 -0.1206 0.3012 1.0000 10.000 1.6024 0.01691 0.01097 -0.1193 0.2954 1.0000 10.250 1.6181 0.01740 0.01148 -0.1176 0.2889 1.0000 10.500 1.6327 0.01797 0.01204 -0.1158 0.2828 1.0000 10.750 1.6478 0.01852 0.01262 -0.1141 0.2757 1.0000 11.000 1.6592 0.01925 0.01335 -0.1120 0.2684 1.0000 11.250 1.6718 0.01996 0.01408 -0.1101 0.2594 1.0000 11.500 1.6808 0.02087 0.01498 -0.1079 0.2499 1.0000 11.750 1.6874 0.02196 0.01605 -0.1055 0.2398 1.0000 12.000 1.6944 0.02310 0.01718 -0.1034 0.2285 1.0000 12.250 1.6995 0.02441 0.01849 -0.1011 0.2182 1.0000 12.500 1.7009 0.02604 0.02009 -0.0988 0.2065 1.0000 12.750 1.7015 0.02783 0.02185 -0.0966 0.1954 1.0000 13.000 1.7045 0.02955 0.02360 -0.0948 0.1858 1.0000 13.250 1.7043 0.03161 0.02566 -0.0930 0.1767 1.0000 13.500 1.7016 0.03400 0.02805 -0.0913 0.1670 1.0000 13.750 1.6992 0.03650 0.03056 -0.0898 0.1569 1.0000 14.000 1.6959 0.03921 0.03329 -0.0885 0.1488 1.0000 14.250 1.6897 0.04232 0.03641 -0.0874 0.1401 1.0000 14.500 1.6852 0.04541 0.03954 -0.0866 0.1321 1.0000 14.750 1.6777 0.04894 0.04309 -0.0859 0.1246 1.0000 15.000 1.6708 0.05254 0.04673 -0.0855 0.1171 1.0000 15.250 1.6627 0.05643 0.05065 -0.0852 0.1105 1.0000 15.500 1.6534 0.06060 0.05486 -0.0852 0.1037 1.0000 15.750 1.6447 0.06481 0.05912 -0.0853 0.0972 1.0000 16.000 1.6333 0.06951 0.06385 -0.0857 0.0907 1.0000 16.250 1.6267 0.07370 0.06810 -0.0862 0.0856 1.0000 16.500 1.6158 0.07856 0.07299 -0.0869 0.0800 1.0000 16.750 1.6080 0.08309 0.07758 -0.0877 0.0748 1.0000 17.000 1.5978 0.08808 0.08261 -0.0888 0.0699 1.0000 17.250 1.5907 0.09267 0.08726 -0.0898 0.0652 1.0000