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 = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.250 -0.7399 0.11578 0.11244 -0.0570 1.0000 0.0110 -19.000 -0.7457 0.11151 0.10811 -0.0589 1.0000 0.0112 -18.750 -0.7536 0.10699 0.10353 -0.0608 1.0000 0.0112 -18.500 -0.7604 0.10265 0.09913 -0.0625 1.0000 0.0114 -18.250 -0.7662 0.09866 0.09508 -0.0641 1.0000 0.0113 -18.000 -0.7735 0.09446 0.09082 -0.0657 1.0000 0.0114 -17.750 -0.7809 0.09034 0.08664 -0.0672 1.0000 0.0114 -17.500 -0.7866 0.08654 0.08278 -0.0685 1.0000 0.0116 -17.250 -0.7934 0.08269 0.07887 -0.0697 1.0000 0.0116 -17.000 -0.8005 0.07890 0.07503 -0.0709 1.0000 0.0116 -16.750 -0.8057 0.07544 0.07150 -0.0718 1.0000 0.0117 -16.500 -0.8121 0.07191 0.06791 -0.0728 1.0000 0.0118 -16.250 -0.8168 0.06873 0.06468 -0.0734 1.0000 0.0119 -16.000 -0.8224 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-0.1035 0.4131 0.4055 -1.250 0.3869 0.00946 0.00308 -0.1032 0.4095 0.4104 -1.000 0.4126 0.00950 0.00312 -0.1027 0.4050 0.4154 -0.750 0.4378 0.00959 0.00317 -0.1020 0.4005 0.4189 -0.500 0.4624 0.00971 0.00325 -0.1014 0.3958 0.4222 -0.250 0.4893 0.00975 0.00328 -0.1011 0.3936 0.4250 0.000 0.5156 0.00982 0.00333 -0.1007 0.3906 0.4274 0.250 0.5413 0.00991 0.00338 -0.1002 0.3873 0.4291 0.500 0.5656 0.00995 0.00343 -0.0995 0.3840 0.4340 0.750 0.5892 0.01006 0.00352 -0.0986 0.3800 0.4380 1.000 0.6134 0.01017 0.00362 -0.0979 0.3767 0.4414 1.250 0.6394 0.01023 0.00368 -0.0975 0.3746 0.4446 1.500 0.6649 0.01030 0.00375 -0.0970 0.3722 0.4475 1.750 0.6899 0.01040 0.00382 -0.0964 0.3696 0.4498 2.000 0.7143 0.01050 0.00390 -0.0958 0.3669 0.4525 2.250 0.7377 0.01060 0.00400 -0.0949 0.3641 0.4575 2.500 0.7603 0.01075 0.00414 -0.0940 0.3607 0.4617 2.750 0.7843 0.01087 0.00426 -0.0933 0.3585 0.4654 3.000 0.8097 0.01094 0.00435 -0.0928 0.3570 0.4688 3.250 0.8346 0.01103 0.00445 -0.0923 0.3552 0.4718 3.500 0.8588 0.01114 0.00455 -0.0916 0.3531 0.4742 3.750 0.8819 0.01123 0.00467 -0.0908 0.3509 0.4798 4.000 0.9045 0.01136 0.00480 -0.0899 0.3488 0.4847 4.250 0.9264 0.01151 0.00496 -0.0889 0.3464 0.4892 4.500 0.9476 0.01172 0.00515 -0.0878 0.3437 0.4933 4.750 0.9691 0.01193 0.00535 -0.0867 0.3412 0.4965 5.000 0.9931 0.01201 0.00547 -0.0861 0.3402 0.5024 5.250 1.0164 0.01211 0.00562 -0.0854 0.3389 0.5081 5.500 1.0391 0.01223 0.00577 -0.0846 0.3374 0.5137 5.750 1.0616 0.01238 0.00593 -0.0838 0.3356 0.5186 6.000 1.0834 0.01252 0.00611 -0.0828 0.3338 0.5256 6.250 1.1047 0.01269 0.00631 -0.0818 0.3321 0.5332 6.500 1.1252 0.01289 0.00652 -0.0807 0.3303 0.5400 6.750 1.1441 0.01313 0.00678 -0.0794 0.3282 0.5475 7.000 1.1620 0.01342 0.00708 -0.0779 0.3256 0.5567 7.250 1.1821 0.01366 0.00735 -0.0768 0.3239 0.5657 7.500 1.2036 0.01379 0.00757 -0.0759 0.3229 0.5780 7.750 1.2243 0.01398 0.00780 -0.0749 0.3217 0.5898 8.000 1.2444 0.01416 0.00806 -0.0739 0.3203 0.6054 8.250 1.2644 0.01436 0.00833 -0.0729 0.3190 0.6217 8.500 1.2835 0.01458 0.00862 -0.0717 0.3175 0.6406 8.750 1.3016 0.01482 0.00895 -0.0704 0.3160 0.6637 9.000 1.3187 0.01508 0.00930 -0.0689 0.3143 0.6939 9.250 1.3336 0.01535 0.00970 -0.0672 0.3127 0.7377 9.500 1.3417 0.01548 0.01018 -0.0640 0.3108 0.8559 9.750 1.3883 0.01588 0.01074 -0.0689 0.3076 1.0000 10.000 1.4080 0.01620 0.01108 -0.0681 0.3068 1.0000 10.250 1.4271 0.01655 0.01147 -0.0672 0.3057 1.0000 10.500 1.4461 0.01692 0.01187 -0.0663 0.3046 1.0000 10.750 1.4643 0.01733 0.01231 -0.0654 0.3033 1.0000 11.000 1.4821 0.01777 0.01278 -0.0645 0.3018 1.0000 11.250 1.4997 0.01823 0.01326 -0.0636 0.3003 1.0000 11.500 1.5159 0.01877 0.01381 -0.0625 0.2988 1.0000 11.750 1.5310 0.01938 0.01443 -0.0614 0.2969 1.0000 12.000 1.5448 0.02007 0.01513 -0.0602 0.2950 1.0000 12.250 1.5582 0.02082 0.01588 -0.0590 0.2927 1.0000 12.500 1.5742 0.02145 0.01654 -0.0582 0.2912 1.0000 12.750 1.5904 0.02208 0.01722 -0.0575 0.2902 1.0000 13.000 1.6069 0.02271 0.01790 -0.0568 0.2890 1.0000 13.250 1.6221 0.02344 0.01868 -0.0560 0.2875 1.0000 13.500 1.6374 0.02419 0.01946 -0.0554 0.2859 1.0000 13.750 1.6518 0.02501 0.02032 -0.0547 0.2842 1.0000 14.000 1.6644 0.02596 0.02129 -0.0539 0.2823 1.0000 14.250 1.6747 0.02708 0.02243 -0.0530 0.2800 1.0000 14.500 1.6838 0.02826 0.02361 -0.0520 0.2770 1.0000 14.750 1.6965 0.02929 0.02469 -0.0515 0.2753 1.0000 15.000 1.7096 0.03036 0.02582 -0.0511 0.2737 1.0000 15.250 1.7221 0.03147 0.02700 -0.0506 0.2717 1.0000 15.500 1.7334 0.03269 0.02826 -0.0502 0.2696 1.0000 15.750 1.7423 0.03410 0.02971 -0.0497 0.2672 1.0000 16.000 1.7488 0.03570 0.03133 -0.0491 0.2650 1.0000 16.250 1.7524 0.03751 0.03315 -0.0483 0.2619 1.0000 16.500 1.7619 0.03894 0.03464 -0.0480 0.2602 1.0000 16.750 1.7703 0.04053 0.03631 -0.0477 0.2582 1.0000 17.000 1.7784 0.04213 0.03798 -0.0474 0.2559 1.0000 17.250 1.7826 0.04406 0.03996 -0.0471 0.2535 1.0000 17.500 1.7835 0.04629 0.04221 -0.0466 0.2505 1.0000 17.750 1.7800 0.04889 0.04481 -0.0460 0.2471 1.0000 18.000 1.7853 0.05080 0.04681 -0.0458 0.2452 1.0000 18.250 1.7882 0.05296 0.04905 -0.0457 0.2429 1.0000 18.500 1.7888 0.05531 0.05146 -0.0454 0.2399 1.0000 18.750 1.7832 0.05826 0.05444 -0.0451 0.2366 1.0000 19.000 1.7722 0.06172 0.05791 -0.0447 0.2329 1.0000 19.250 1.7737 0.06408 0.06036 -0.0447 0.2303 1.0000