XFOIL Version 6.96 Calculated polar for: EPPLER 399 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 ------ -------- --------- --------- -------- -------- -------- -14.500 -0.4724 0.10651 0.10395 -0.0630 1.0000 0.0100 -14.250 -0.5080 0.09583 0.09315 -0.0678 1.0000 0.0098 -14.000 -0.5358 0.08743 0.08464 -0.0716 1.0000 0.0096 -13.750 -0.5609 0.08020 0.07730 -0.0748 1.0000 0.0095 -13.500 -0.5831 0.07422 0.07124 -0.0770 1.0000 0.0093 -13.250 -0.6069 0.06902 0.06597 -0.0783 1.0000 0.0093 -13.000 -0.6159 0.06187 0.05867 -0.0855 0.9980 0.0093 -12.750 -0.6162 0.05516 0.05177 -0.0938 0.9946 0.0091 -12.500 -0.6138 0.04906 0.04551 -0.1016 0.9901 0.0093 -12.250 -0.6056 0.04365 0.03993 -0.1095 0.9849 0.0094 -12.000 -0.5967 0.03880 0.03492 -0.1164 0.9777 0.0093 -11.750 -0.5812 0.03437 0.03032 -0.1239 0.9708 0.0095 -11.500 -0.5696 0.03050 0.02628 -0.1297 0.9590 0.0097 -11.250 -0.5517 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0.4871 0.00912 0.00281 -0.1602 0.6757 0.3884 -1.500 0.5157 0.00910 0.00281 -0.1604 0.6713 0.4027 -1.250 0.5445 0.00912 0.00282 -0.1606 0.6673 0.4171 -1.000 0.5732 0.00914 0.00285 -0.1608 0.6632 0.4314 -0.750 0.6015 0.00913 0.00288 -0.1610 0.6589 0.4464 -0.500 0.6299 0.00913 0.00291 -0.1611 0.6548 0.4619 -0.250 0.6587 0.00917 0.00293 -0.1613 0.6509 0.4780 0.000 0.6873 0.00922 0.00300 -0.1616 0.6470 0.4947 0.250 0.7154 0.00921 0.00306 -0.1617 0.6429 0.5119 0.500 0.7437 0.00922 0.00312 -0.1618 0.6388 0.5298 0.750 0.7721 0.00926 0.00317 -0.1620 0.6350 0.5483 1.000 0.8008 0.00933 0.00327 -0.1622 0.6312 0.5677 1.250 0.8285 0.00934 0.00336 -0.1622 0.6271 0.5876 1.500 0.8564 0.00936 0.00345 -0.1623 0.6230 0.6084 1.750 0.8845 0.00941 0.00352 -0.1624 0.6191 0.6300 2.000 0.9129 0.00950 0.00364 -0.1625 0.6152 0.6517 2.250 0.9400 0.00951 0.00377 -0.1624 0.6111 0.6743 2.500 0.9673 0.00954 0.00387 -0.1623 0.6068 0.6980 2.750 0.9946 0.00958 0.00397 -0.1623 0.6027 0.7215 3.000 1.0222 0.00968 0.00412 -0.1622 0.5986 0.7469 3.250 1.0480 0.00969 0.00425 -0.1618 0.5942 0.7729 3.500 1.0738 0.00971 0.00437 -0.1614 0.5896 0.8008 3.750 1.0992 0.00977 0.00448 -0.1609 0.5852 0.8315 4.000 1.1224 0.00980 0.00462 -0.1599 0.5806 0.8664 4.250 1.1405 0.00972 0.00469 -0.1576 0.5755 0.9163 4.500 1.1656 0.00970 0.00470 -0.1571 0.5703 1.0000 4.750 1.1932 0.00985 0.00483 -0.1572 0.5649 1.0000 5.000 1.2195 0.00994 0.00496 -0.1570 0.5589 1.0000 5.250 1.2462 0.01008 0.00508 -0.1569 0.5530 1.0000 5.500 1.2722 0.01021 0.00524 -0.1567 0.5470 1.0000 5.750 1.2975 0.01032 0.00538 -0.1563 0.5402 1.0000 6.000 1.3229 0.01050 0.00553 -0.1559 0.5336 1.0000 6.250 1.3473 0.01060 0.00570 -0.1554 0.5258 1.0000 6.500 1.3714 0.01080 0.00586 -0.1548 0.5182 1.0000 6.750 1.3948 0.01092 0.00606 -0.1540 0.5091 1.0000 7.000 1.4174 0.01112 0.00625 -0.1532 0.5001 1.0000 7.250 1.4393 0.01132 0.00646 -0.1521 0.4898 1.0000 7.500 1.4604 0.01153 0.00670 -0.1510 0.4785 1.0000 7.750 1.4800 0.01179 0.00696 -0.1496 0.4663 1.0000 8.000 1.4972 0.01209 0.00724 -0.1477 0.4530 1.0000 8.250 1.5114 0.01244 0.00757 -0.1452 0.4374 1.0000 8.500 1.5240 0.01286 0.00796 -0.1426 0.4196 1.0000 8.750 1.5339 0.01339 0.00843 -0.1395 0.3983 1.0000 9.000 1.5407 0.01409 0.00903 -0.1361 0.3755 1.0000 9.250 1.5467 0.01488 0.00973 -0.1326 0.3501 1.0000 9.500 1.5506 0.01582 0.01058 -0.1290 0.3260 1.0000 9.750 1.5528 0.01692 0.01156 -0.1254 0.3009 1.0000 10.000 1.5542 0.01814 0.01269 -0.1219 0.2766 1.0000 10.250 1.5538 0.01957 0.01401 -0.1184 0.2529 1.0000 10.500 1.5537 0.02109 0.01544 -0.1152 0.2298 1.0000 10.750 1.5528 0.02279 0.01704 -0.1121 0.2082 1.0000 11.000 1.5520 0.02460 0.01877 -0.1093 0.1882 1.0000 11.250 1.5512 0.02652 0.02062 -0.1068 0.1686 1.0000 11.500 1.5504 0.02855 0.02258 -0.1045 0.1511 1.0000 11.750 1.5495 0.03070 0.02466 -0.1023 0.1350 1.0000 12.250 1.5484 0.03522 0.02909 -0.0987 0.1064 1.0000 12.500 1.5483 0.03759 0.03143 -0.0971 0.0942 1.0000 12.750 1.5480 0.04007 0.03387 -0.0957 0.0828 1.0000 13.000 1.5480 0.04260 0.03638 -0.0945 0.0726 1.0000 13.250 1.5485 0.04518 0.03894 -0.0934 0.0636 1.0000 13.500 1.5494 0.04779 0.04156 -0.0925 0.0558 1.0000 13.750 1.5497 0.05053 0.04431 -0.0917 0.0488 1.0000 14.000 1.5504 0.05333 0.04712 -0.0910 0.0431 1.0000 14.250 1.5502 0.05629 0.05009 -0.0904 0.0381 1.0000 14.500 1.5507 0.05926 0.05309 -0.0899 0.0339 1.0000 14.750 1.5516 0.06225 0.05613 -0.0896 0.0303 1.0000 15.000 1.5507 0.06552 0.05945 -0.0893 0.0273 1.0000 15.250 1.5519 0.06861 0.06259 -0.0892 0.0247 1.0000 15.500 1.5515 0.07197 0.06601 -0.0892 0.0224 1.0000 15.750 1.5514 0.07536 0.06945 -0.0893 0.0205 1.0000 16.000 1.5508 0.07888 0.07304 -0.0895 0.0187 1.0000 16.250 1.5506 0.08242 0.07666 -0.0899 0.0172 1.0000 16.500 1.5477 0.08640 0.08072 -0.0904 0.0159 1.0000 16.750 1.5484 0.08991 0.08431 -0.0909 0.0146 1.0000 17.000 1.5430 0.09441 0.08887 -0.0917 0.0136 1.0000 17.250 1.5429 0.09815 0.09272 -0.0925 0.0125 1.0000 17.500 1.5414 0.10215 0.09680 -0.0934 0.0116 1.0000 17.750 1.5336 0.10721 0.10193 -0.0947 0.0109 1.0000 18.000 1.5337 0.11106 0.10590 -0.0958 0.0102 1.0000 18.250 1.5314 0.11532 0.11026 -0.0971 0.0095 1.0000 18.500 1.5262 0.12012 0.11514 -0.0988 0.0090 1.0000