XFOIL Version 6.96 Calculated polar for: EPPLER 67 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.500 -0.4170 0.09458 0.08980 -0.0449 1.0000 0.0255 -9.250 -0.4322 0.09021 0.08552 -0.0449 1.0000 0.0251 -9.000 -0.4538 0.08505 0.08047 -0.0451 1.0000 0.0247 -8.750 -0.5181 0.07112 0.06663 -0.0498 1.0000 0.0232 -8.500 -0.5343 0.06164 0.05703 -0.0618 0.9927 0.0230 -8.250 -0.5346 0.05276 0.04770 -0.0727 0.9837 0.0228 -8.000 -0.5301 0.04646 0.04085 -0.0777 0.9755 0.0229 -7.750 -0.5135 0.04108 0.03479 -0.0819 0.9704 0.0231 -7.500 -0.4971 0.03736 0.03064 -0.0833 0.9644 0.0236 -7.250 -0.4714 0.03493 0.02795 -0.0854 0.9605 0.0247 -7.000 -0.4449 0.03313 0.02587 -0.0869 0.9565 0.0263 -6.750 -0.4209 0.03127 0.02366 -0.0875 0.9513 0.0284 -6.500 -0.3912 0.02918 0.02109 -0.0888 0.9478 0.0302 -6.250 -0.3596 0.02721 0.01886 -0.0903 0.9453 0.0320 -6.000 -0.3373 0.02603 0.01759 -0.0900 0.9394 0.0339 -5.750 -0.3074 0.02485 0.01625 -0.0909 0.9354 0.0379 -5.500 -0.2744 0.02380 0.01509 -0.0926 0.9325 0.0448 -5.250 -0.2482 0.02292 0.01406 -0.0927 0.9273 0.0531 -5.000 -0.2192 0.02214 0.01327 -0.0935 0.9226 0.0667 -4.750 -0.1858 0.02144 0.01255 -0.0951 0.9194 0.0855 -4.500 -0.1549 0.02082 0.01193 -0.0961 0.9154 0.1067 -4.250 -0.1287 0.02034 0.01145 -0.0962 0.9094 0.1301 -4.000 -0.0953 0.01981 0.01095 -0.0976 0.9059 0.1593 -3.750 -0.0593 0.01930 0.01052 -0.0995 0.9034 0.1958 -3.500 -0.0371 0.01902 0.01031 -0.0988 0.8959 0.2297 -3.250 -0.0040 0.01862 0.00999 -0.1000 0.8921 0.2746 -3.000 0.0319 0.01821 0.00969 -0.1018 0.8895 0.3253 -2.750 0.0546 0.01803 0.00962 -0.1010 0.8820 0.3692 -2.500 0.0872 0.01773 0.00943 -0.1020 0.8780 0.4217 -2.250 0.1229 0.01741 0.00920 -0.1034 0.8754 0.4750 -2.000 0.1447 0.01734 0.00923 -0.1022 0.8675 0.5187 -1.750 0.1770 0.01712 0.00910 -0.1028 0.8635 0.5668 -1.500 0.2126 0.01687 0.00891 -0.1040 0.8607 0.6139 -1.250 0.2325 0.01688 0.00899 -0.1023 0.8521 0.6521 -1.000 0.2653 0.01669 0.00885 -0.1028 0.8482 0.6941 -0.750 0.2895 0.01663 0.00884 -0.1017 0.8416 0.7316 -0.500 0.3162 0.01651 0.00876 -0.1009 0.8356 0.7698 -0.250 0.3477 0.01627 0.00856 -0.1009 0.8321 0.8081 0.000 0.3644 0.01628 0.00862 -0.0983 0.8228 0.8460 0.250 0.3957 0.01603 0.00838 -0.0983 0.8186 0.8886 0.500 0.4253 0.01597 0.00834 -0.0984 0.8107 0.9410 0.750 0.4697 0.01575 0.00807 -0.1018 0.8057 1.0000 1.000 0.4986 0.01579 0.00803 -0.1022 0.7980 1.0000 1.250 0.5318 0.01573 0.00790 -0.1032 0.7915 1.0000 1.500 0.5604 0.01577 0.00790 -0.1035 0.7833 1.0000 1.750 0.5941 0.01570 0.00778 -0.1045 0.7764 1.0000 2.000 0.6209 0.01578 0.00783 -0.1044 0.7671 1.0000 2.250 0.6570 0.01566 0.00769 -0.1058 0.7605 1.0000 2.500 0.6818 0.01578 0.00781 -0.1052 0.7497 1.0000 2.750 0.7108 0.01582 0.00784 -0.1054 0.7401 1.0000 3.000 0.7446 0.01575 0.00775 -0.1063 0.7315 1.0000 3.250 0.7699 0.01586 0.00790 -0.1058 0.7198 1.0000 3.500 0.7970 0.01594 0.00800 -0.1055 0.7080 1.0000 3.750 0.8250 0.01600 0.00807 -0.1054 0.6958 1.0000 4.000 0.8531 0.01606 0.00815 -0.1053 0.6830 1.0000 4.250 0.8805 0.01615 0.00827 -0.1050 0.6692 1.0000 4.500 0.9070 0.01626 0.00841 -0.1046 0.6543 1.0000 4.750 0.9327 0.01639 0.00856 -0.1040 0.6383 1.0000 5.000 0.9580 0.01654 0.00873 -0.1034 0.6212 1.0000 5.250 0.9834 0.01670 0.00892 -0.1027 0.6031 1.0000 5.500 1.0067 0.01692 0.00916 -0.1017 0.5834 1.0000 5.750 1.0291 0.01717 0.00941 -0.1006 0.5620 1.0000 6.000 1.0510 0.01745 0.00969 -0.0993 0.5393 1.0000 6.250 1.0719 0.01778 0.01002 -0.0979 0.5149 1.0000 6.500 1.0909 0.01817 0.01039 -0.0963 0.4883 1.0000 6.750 1.1088 0.01862 0.01079 -0.0944 0.4601 1.0000 7.000 1.1251 0.01914 0.01124 -0.0923 0.4300 1.0000 7.250 1.1396 0.01974 0.01175 -0.0900 0.3988 1.0000 7.500 1.1519 0.02039 0.01235 -0.0874 0.3666 1.0000 7.750 1.1626 0.02114 0.01300 -0.0846 0.3342 1.0000 8.000 1.1723 0.02199 0.01373 -0.0818 0.3020 1.0000 8.250 1.1813 0.02293 0.01456 -0.0790 0.2708 1.0000 8.500 1.1897 0.02395 0.01547 -0.0762 0.2411 1.0000 8.750 1.1980 0.02504 0.01647 -0.0736 0.2132 1.0000 9.000 1.2059 0.02621 0.01755 -0.0711 0.1865 1.0000 9.250 1.2135 0.02745 0.01875 -0.0686 0.1618 1.0000 9.500 1.2202 0.02879 0.02001 -0.0662 0.1396 1.0000 9.750 1.2268 0.03021 0.02136 -0.0639 0.1186 1.0000 10.000 1.2327 0.03173 0.02282 -0.0617 0.1012 1.0000 10.250 1.2390 0.03328 0.02436 -0.0597 0.0856 1.0000 10.500 1.2443 0.03495 0.02603 -0.0576 0.0728 1.0000 10.750 1.2481 0.03679 0.02787 -0.0556 0.0629 1.0000 11.000 1.2519 0.03870 0.02983 -0.0538 0.0547 1.0000 11.250 1.2549 0.04076 0.03199 -0.0519 0.0488 1.0000 11.500 1.2564 0.04299 0.03432 -0.0502 0.0441 1.0000 11.750 1.2576 0.04535 0.03678 -0.0486 0.0400 1.0000 12.000 1.2603 0.04763 0.03919 -0.0473 0.0362 1.0000 12.250 1.2594 0.05032 0.04195 -0.0462 0.0337 1.0000 12.500 1.2594 0.05309 0.04485 -0.0450 0.0318 1.0000 12.750 1.2616 0.05574 0.04770 -0.0440 0.0300 1.0000 13.000 1.2633 0.05850 0.05062 -0.0432 0.0283 1.0000 13.250 1.2637 0.06142 0.05365 -0.0428 0.0267 1.0000 13.500 1.2619 0.06466 0.05698 -0.0425 0.0254 1.0000 13.750 1.2612 0.06800 0.06045 -0.0423 0.0241 1.0000 14.000 1.2622 0.07127 0.06397 -0.0421 0.0231 1.0000 14.250 1.2621 0.07479 0.06772 -0.0421 0.0222 1.0000 14.500 1.2605 0.07859 0.07173 -0.0423 0.0215 1.0000 14.750 1.2574 0.08267 0.07602 -0.0429 0.0208 1.0000 15.000 1.2529 0.08702 0.08060 -0.0438 0.0203 1.0000 15.250 1.2472 0.09161 0.08536 -0.0452 0.0198 1.0000 15.500 1.2407 0.09645 0.09037 -0.0469 0.0193 1.0000 15.750 1.2334 0.10153 0.09559 -0.0489 0.0188 1.0000 16.000 1.2254 0.10689 0.10108 -0.0512 0.0184 1.0000 16.500 1.2027 0.11963 0.11421 -0.0576 0.0179 1.0000 16.750 1.1881 0.12720 0.12202 -0.0621 0.0178 1.0000 17.000 1.1730 0.13523 0.13027 -0.0670 0.0178 1.0000 17.250 1.1568 0.14398 0.13921 -0.0727 0.0178 1.0000 17.500 1.1398 0.15340 0.14880 -0.0790 0.0179 1.0000