XFOIL Version 6.96 Calculated polar for: E212 (10.55%) 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 ------ -------- --------- --------- -------- -------- -------- -10.000 -0.4625 0.09346 0.08826 -0.0406 1.0000 0.0247 -9.750 -0.4976 0.08040 0.07529 -0.0466 1.0000 0.0236 -9.500 -0.5136 0.07403 0.06897 -0.0493 1.0000 0.0233 -9.250 -0.5365 0.06706 0.06203 -0.0529 1.0000 0.0231 -9.000 -0.5618 0.06161 0.05663 -0.0553 1.0000 0.0228 -8.750 -0.5866 0.05652 0.05148 -0.0584 1.0000 0.0226 -8.500 -0.6032 0.05149 0.04623 -0.0607 1.0000 0.0225 -8.250 -0.6107 0.04686 0.04128 -0.0621 1.0000 0.0225 -8.000 -0.6094 0.04264 0.03666 -0.0631 1.0000 0.0225 -7.750 -0.6008 0.03885 0.03239 -0.0638 1.0000 0.0226 -7.500 -0.5868 0.03553 0.02855 -0.0644 1.0000 0.0232 -7.250 -0.5690 0.03288 0.02544 -0.0647 1.0000 0.0239 -7.000 -0.5502 0.03111 0.02357 -0.0647 1.0000 0.0249 -6.750 -0.5294 0.02944 0.02168 -0.0647 1.0000 0.0258 -6.500 -0.5074 0.02772 0.01972 -0.0646 1.0000 0.0265 -6.250 -0.4844 0.02617 0.01792 -0.0645 1.0000 0.0274 -6.000 -0.4608 0.02484 0.01641 -0.0643 1.0000 0.0283 -5.750 -0.4367 0.02368 0.01506 -0.0642 1.0000 0.0294 -5.500 -0.4080 0.02251 0.01381 -0.0652 0.9988 0.0312 -5.250 -0.3722 0.02164 0.01282 -0.0675 0.9955 0.0350 -5.000 -0.3366 0.02069 0.01177 -0.0698 0.9920 0.0412 -4.750 -0.3001 0.01969 0.01072 -0.0721 0.9884 0.0538 -4.500 -0.2627 0.01875 0.00992 -0.0748 0.9853 0.0919 -4.250 -0.2284 0.01806 0.00951 -0.0770 0.9809 0.1550 -4.000 -0.1927 0.01760 0.00926 -0.0793 0.9763 0.2149 -3.750 -0.1562 0.01731 0.00901 -0.0815 0.9721 0.2576 -3.500 -0.1232 0.01703 0.00877 -0.0828 0.9661 0.2964 -3.250 -0.0860 0.01683 0.00860 -0.0849 0.9616 0.3363 -3.000 -0.0544 0.01662 0.00844 -0.0859 0.9547 0.3710 -2.750 -0.0181 0.01646 0.00828 -0.0877 0.9496 0.4067 -2.500 0.0136 0.01630 0.00815 -0.0885 0.9425 0.4397 -2.250 0.0488 0.01614 0.00803 -0.0900 0.9366 0.4729 -2.000 0.0812 0.01600 0.00791 -0.0908 0.9295 0.5038 -1.750 0.1155 0.01585 0.00780 -0.0920 0.9229 0.5344 -1.500 0.1484 0.01570 0.00770 -0.0928 0.9159 0.5635 -1.250 0.1816 0.01555 0.00759 -0.0936 0.9086 0.5921 -1.000 0.2146 0.01539 0.00748 -0.0944 0.9015 0.6203 -0.750 0.2476 0.01522 0.00735 -0.0950 0.8939 0.6483 -0.500 0.2798 0.01506 0.00724 -0.0955 0.8858 0.6757 -0.250 0.3134 0.01488 0.00712 -0.0962 0.8782 0.7029 0.000 0.3433 0.01474 0.00704 -0.0961 0.8684 0.7294 0.250 0.3788 0.01452 0.00687 -0.0970 0.8612 0.7571 0.500 0.4059 0.01440 0.00680 -0.0964 0.8494 0.7839 0.750 0.4338 0.01423 0.00670 -0.0957 0.8380 0.8111 1.000 0.4628 0.01403 0.00655 -0.0953 0.8269 0.8398 1.250 0.4921 0.01380 0.00636 -0.0948 0.8154 0.8710 1.500 0.5189 0.01359 0.00621 -0.0939 0.8013 0.9085 1.750 0.5548 0.01336 0.00601 -0.0951 0.7865 0.9680 2.000 0.5913 0.01330 0.00590 -0.0967 0.7704 1.0000 2.250 0.6241 0.01335 0.00591 -0.0976 0.7525 1.0000 2.500 0.6565 0.01341 0.00594 -0.0983 0.7336 1.0000 2.750 0.6885 0.01350 0.00597 -0.0989 0.7140 1.0000 3.000 0.7198 0.01362 0.00605 -0.0994 0.6936 1.0000 3.250 0.7486 0.01379 0.00618 -0.0994 0.6709 1.0000 3.500 0.7777 0.01398 0.00630 -0.0995 0.6479 1.0000 3.750 0.8049 0.01421 0.00650 -0.0992 0.6230 1.0000 4.000 0.8316 0.01447 0.00670 -0.0988 0.5976 1.0000 4.250 0.8578 0.01477 0.00693 -0.0983 0.5716 1.0000 4.500 0.8829 0.01510 0.00719 -0.0977 0.5441 1.0000 4.750 0.9074 0.01545 0.00752 -0.0969 0.5159 1.0000 5.000 0.9312 0.01585 0.00785 -0.0961 0.4866 1.0000 5.250 0.9543 0.01629 0.00822 -0.0951 0.4566 1.0000 5.500 0.9768 0.01676 0.00864 -0.0941 0.4262 1.0000 5.750 0.9987 0.01728 0.00909 -0.0930 0.3954 1.0000 6.000 1.0201 0.01783 0.00958 -0.0919 0.3644 1.0000 6.250 1.0407 0.01844 0.01011 -0.0907 0.3328 1.0000 6.500 1.0607 0.01911 0.01071 -0.0894 0.3009 1.0000 6.750 1.0802 0.01983 0.01135 -0.0881 0.2688 1.0000 7.000 1.0992 0.02060 0.01205 -0.0868 0.2378 1.0000 7.250 1.1176 0.02142 0.01280 -0.0854 0.2083 1.0000 7.500 1.1352 0.02233 0.01362 -0.0840 0.1787 1.0000 7.750 1.1515 0.02335 0.01452 -0.0825 0.1466 1.0000 8.000 1.1663 0.02451 0.01547 -0.0809 0.1141 1.0000 8.250 1.1811 0.02570 0.01649 -0.0793 0.0864 1.0000 8.500 1.1961 0.02685 0.01762 -0.0776 0.0668 1.0000 8.750 1.2082 0.02823 0.01894 -0.0756 0.0516 1.0000 9.000 1.2175 0.02972 0.02046 -0.0730 0.0409 1.0000 9.250 1.2255 0.03126 0.02205 -0.0704 0.0345 1.0000 9.500 1.2330 0.03281 0.02372 -0.0678 0.0305 1.0000 9.750 1.2403 0.03434 0.02535 -0.0654 0.0275 1.0000 10.000 1.2448 0.03612 0.02722 -0.0628 0.0256 1.0000 10.250 1.2503 0.03787 0.02917 -0.0605 0.0243 1.0000 10.500 1.2550 0.03976 0.03122 -0.0582 0.0233 1.0000 10.750 1.2590 0.04177 0.03338 -0.0562 0.0224 1.0000 11.000 1.2624 0.04391 0.03567 -0.0544 0.0217 1.0000 11.250 1.2650 0.04622 0.03810 -0.0527 0.0212 1.0000 11.500 1.2666 0.04878 0.04077 -0.0513 0.0207 1.0000 11.750 1.2701 0.05141 0.04356 -0.0500 0.0203 1.0000 12.000 1.2736 0.05417 0.04655 -0.0489 0.0199 1.0000 12.250 1.2755 0.05715 0.04979 -0.0479 0.0195 1.0000 12.500 1.2752 0.06039 0.05327 -0.0473 0.0190 1.0000 12.750 1.2728 0.06391 0.05703 -0.0470 0.0186 1.0000 13.000 1.2685 0.06773 0.06109 -0.0470 0.0182 1.0000 13.250 1.2621 0.07190 0.06549 -0.0476 0.0178 1.0000 13.500 1.2542 0.07646 0.07028 -0.0486 0.0176 1.0000 13.750 1.2446 0.08146 0.07549 -0.0501 0.0173 1.0000 14.000 1.2332 0.08696 0.08122 -0.0523 0.0172 1.0000 14.250 1.2201 0.09311 0.08762 -0.0551 0.0171 1.0000 14.500 1.2048 0.10005 0.09480 -0.0588 0.0171 1.0000 14.750 1.1866 0.10806 0.10304 -0.0635 0.0171 1.0000 15.000 1.1644 0.11764 0.11288 -0.0695 0.0173 1.0000 15.250 1.1354 0.12988 0.12538 -0.0777 0.0178 1.0000 15.500 1.0937 0.14748 0.14324 -0.0895 0.0188 1.0000