XFOIL Version 6.96 Calculated polar for: EPPLER 858 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.250 -0.5268 0.13681 0.13210 -0.0509 1.0000 0.0192 -18.000 -0.5522 0.12796 0.12307 -0.0551 1.0000 0.0193 -17.750 -0.5674 0.12144 0.11643 -0.0580 1.0000 0.0195 -17.500 -0.5823 0.11518 0.11003 -0.0609 1.0000 0.0199 -17.250 -0.5912 0.11021 0.10495 -0.0629 1.0000 0.0200 -17.000 -0.5987 0.10561 0.10025 -0.0647 1.0000 0.0202 -16.750 -0.6056 0.10121 0.09574 -0.0664 1.0000 0.0205 -16.500 -0.6101 0.09739 0.09188 -0.0677 1.0000 0.0207 -16.250 -0.6135 0.09386 0.08834 -0.0688 1.0000 0.0210 -16.000 -0.6170 0.09036 0.08479 -0.0699 1.0000 0.0212 -15.750 -0.6206 0.08692 0.08132 -0.0709 1.0000 0.0215 -15.500 -0.6243 0.08357 0.07793 -0.0718 1.0000 0.0217 -15.250 -0.6284 0.08025 0.07457 -0.0725 1.0000 0.0221 -15.000 -0.6316 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0.4388 0.4524 -0.500 0.4397 0.01640 0.00691 -0.0975 0.4349 0.4558 -0.250 0.4637 0.01645 0.00697 -0.0967 0.4307 0.4591 0.000 0.4877 0.01651 0.00702 -0.0960 0.4267 0.4627 0.250 0.5114 0.01660 0.00706 -0.0952 0.4229 0.4665 0.500 0.5350 0.01671 0.00710 -0.0944 0.4195 0.4706 0.750 0.5588 0.01685 0.00714 -0.0937 0.4163 0.4745 1.000 0.5827 0.01694 0.00725 -0.0930 0.4132 0.4780 1.250 0.6060 0.01703 0.00737 -0.0922 0.4097 0.4816 1.500 0.6289 0.01714 0.00748 -0.0913 0.4061 0.4854 1.750 0.6518 0.01728 0.00759 -0.0904 0.4027 0.4896 2.000 0.6749 0.01745 0.00769 -0.0896 0.3997 0.4941 2.250 0.6987 0.01763 0.00782 -0.0890 0.3970 0.4983 2.500 0.7222 0.01779 0.00800 -0.0883 0.3945 0.5025 2.750 0.7451 0.01794 0.00820 -0.0875 0.3918 0.5068 3.000 0.7678 0.01811 0.00839 -0.0866 0.3891 0.5113 3.250 0.7901 0.01830 0.00858 -0.0857 0.3863 0.5161 3.500 0.8122 0.01850 0.00876 -0.0848 0.3836 0.5210 3.750 0.8340 0.01868 0.00895 -0.0839 0.3811 0.5259 4.000 0.8567 0.01890 0.00915 -0.0831 0.3786 0.5315 4.250 0.8797 0.01914 0.00938 -0.0824 0.3763 0.5373 4.500 0.9010 0.01936 0.00965 -0.0815 0.3741 0.5430 4.750 0.9218 0.01957 0.00994 -0.0804 0.3718 0.5483 5.000 0.9425 0.01980 0.01023 -0.0794 0.3696 0.5547 5.250 0.9631 0.02005 0.01051 -0.0783 0.3673 0.5622 5.500 0.9834 0.02029 0.01078 -0.0772 0.3651 0.5693 5.750 1.0041 0.02054 0.01106 -0.0762 0.3630 0.5773 6.000 1.0258 0.02081 0.01132 -0.0754 0.3609 0.5859 6.250 1.0488 0.02110 0.01161 -0.0749 0.3589 0.5945 6.500 1.0661 0.02140 0.01203 -0.0734 0.3570 0.6043 6.750 1.0841 0.02172 0.01245 -0.0721 0.3550 0.6155 7.000 1.1021 0.02204 0.01287 -0.0708 0.3530 0.6285 7.250 1.1197 0.02236 0.01329 -0.0694 0.3511 0.6427 7.500 1.1367 0.02269 0.01371 -0.0680 0.3491 0.6591 7.750 1.1533 0.02301 0.01412 -0.0665 0.3471 0.6779 8.000 1.1717 0.02332 0.01451 -0.0654 0.3452 0.7012 8.250 1.1920 0.02362 0.01490 -0.0645 0.3434 0.7326 8.500 1.2150 0.02386 0.01526 -0.0641 0.3416 0.7868 8.750 1.2422 0.02413 0.01587 -0.0650 0.3398 1.0000 9.000 1.2558 0.02471 0.01652 -0.0635 0.3380 1.0000 9.250 1.2698 0.02531 0.01717 -0.0620 0.3362 1.0000 9.500 1.2831 0.02594 0.01784 -0.0606 0.3342 1.0000 9.750 1.2970 0.02657 0.01850 -0.0592 0.3323 1.0000 10.000 1.3108 0.02720 0.01916 -0.0579 0.3303 1.0000 10.250 1.3255 0.02782 0.01978 -0.0568 0.3285 1.0000 10.500 1.3426 0.02840 0.02036 -0.0559 0.3269 1.0000 10.750 1.3627 0.02892 0.02086 -0.0555 0.3254 1.0000 11.000 1.3809 0.02956 0.02150 -0.0548 0.3239 1.0000 11.250 1.3842 0.03070 0.02277 -0.0527 0.3221 1.0000 11.500 1.3879 0.03190 0.02408 -0.0508 0.3202 1.0000 11.750 1.3918 0.03315 0.02543 -0.0490 0.3180 1.0000 12.000 1.3976 0.03437 0.02672 -0.0476 0.3159 1.0000 12.250 1.4052 0.03553 0.02794 -0.0463 0.3140 1.0000 12.500 1.4147 0.03663 0.02909 -0.0453 0.3122 1.0000 12.750 1.4265 0.03763 0.03012 -0.0445 0.3107 1.0000 13.000 1.4436 0.03835 0.03084 -0.0441 0.3092 1.0000 13.250 1.4668 0.03877 0.03121 -0.0441 0.3077 1.0000 13.500 1.4441 0.04203 0.03471 -0.0416 0.3052 1.0000 13.750 1.4244 0.04544 0.03831 -0.0397 0.3023 1.0000 14.000 1.4122 0.04856 0.04157 -0.0385 0.2996 1.0000 14.250 1.4084 0.05111 0.04420 -0.0378 0.2973 1.0000 14.500 1.4130 0.05297 0.04611 -0.0374 0.2953 1.0000 14.750 1.4280 0.05389 0.04703 -0.0372 0.2935 1.0000 15.000 1.4513 0.05410 0.04722 -0.0372 0.2922 1.0000 15.500 1.2258 0.08469 0.07850 -0.0382 0.2742 1.0000 15.750 1.2711 0.08184 0.07562 -0.0377 0.2749 1.0000