XFOIL Version 6.96 Calculated polar for: GOE 627 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.500 -0.4533 0.09073 0.08759 -0.0380 1.0000 0.0776 -9.250 -0.4512 0.08955 0.08645 -0.0351 1.0000 0.0784 -9.000 -0.4575 0.08700 0.08394 -0.0345 0.9995 0.0794 -8.750 -0.4534 0.08112 0.07805 -0.0423 0.9944 0.0817 -8.500 -0.4785 0.07404 0.07084 -0.0494 0.9848 0.0837 -8.000 -0.4923 0.06195 0.05833 -0.0558 0.9668 0.0902 -7.750 -0.4756 0.05947 0.05581 -0.0563 0.9597 0.0931 -7.500 -0.4872 0.05447 0.05029 -0.0559 0.9488 0.1010 -7.250 -0.5019 0.04153 0.03572 -0.0515 0.9406 0.0660 -7.000 -0.5024 0.03630 0.02963 -0.0468 0.9306 0.0585 -6.750 -0.4708 0.03385 0.02696 -0.0478 0.9267 0.0577 -6.500 -0.4357 0.03197 0.02471 -0.0491 0.9239 0.0580 -6.250 -0.4204 0.03051 0.02301 -0.0467 0.9138 0.0583 -6.000 -0.3839 0.02829 0.02063 -0.0484 0.9104 0.0589 -5.750 -0.3411 0.02659 0.01879 -0.0510 0.9082 0.0593 -5.500 -0.3203 0.02555 0.01768 -0.0494 0.8982 0.0600 -5.250 -0.2792 0.02440 0.01651 -0.0516 0.8946 0.0618 -5.000 -0.2350 0.02327 0.01530 -0.0543 0.8922 0.0636 -4.750 -0.2117 0.02248 0.01445 -0.0530 0.8827 0.0647 -4.500 -0.1705 0.02148 0.01338 -0.0550 0.8788 0.0661 -4.250 -0.1266 0.02013 0.01210 -0.0577 0.8766 0.0683 -4.000 -0.1020 0.01939 0.01143 -0.0567 0.8678 0.0710 -3.750 -0.0646 0.01848 0.01052 -0.0580 0.8632 0.0743 -3.500 -0.0221 0.01738 0.00946 -0.0604 0.8603 0.0785 -3.250 0.0014 0.01672 0.00882 -0.0591 0.8508 0.0835 -3.000 0.0396 0.01578 0.00794 -0.0606 0.8451 0.0963 -2.750 0.0595 0.01435 0.00726 -0.0590 0.8359 0.2290 -2.500 0.0802 0.01299 0.00672 -0.0574 0.8271 0.4288 -2.250 0.0929 0.01215 0.00647 -0.0538 0.8147 0.5737 -2.000 0.1253 0.01142 0.00633 -0.0535 0.8052 0.7324 -1.750 0.1706 0.01126 0.00633 -0.0557 0.7930 0.8177 -1.500 0.2208 0.01144 0.00649 -0.0589 0.7787 0.8714 -1.250 0.2699 0.01173 0.00666 -0.0618 0.7627 0.9028 -1.000 0.3367 0.01223 0.00697 -0.0682 0.7446 0.9205 -0.750 0.4038 0.01260 0.00711 -0.0753 0.7240 0.9267 -0.500 0.4442 0.01285 0.00717 -0.0773 0.7022 0.9383 -0.250 0.4954 0.01309 0.00720 -0.0816 0.6766 0.9450 0.000 0.5311 0.01329 0.00719 -0.0829 0.6526 0.9547 0.250 0.5731 0.01343 0.00714 -0.0857 0.6264 0.9608 0.500 0.6072 0.01362 0.00712 -0.0869 0.6011 0.9696 0.750 0.6513 0.01374 0.00706 -0.0903 0.5727 0.9775 1.000 0.6979 0.01386 0.00694 -0.0942 0.5430 0.9869 1.250 0.7442 0.01393 0.00678 -0.0983 0.5124 0.9960 1.500 0.7741 0.01403 0.00670 -0.0991 0.4879 1.0000 1.750 0.7855 0.01423 0.00676 -0.0963 0.4689 1.0000 2.000 0.7973 0.01445 0.00684 -0.0935 0.4522 1.0000 2.250 0.8092 0.01468 0.00695 -0.0907 0.4369 1.0000 2.500 0.8212 0.01495 0.00706 -0.0879 0.4235 1.0000 2.750 0.8339 0.01516 0.00720 -0.0852 0.4105 1.0000 3.000 0.8466 0.01540 0.00736 -0.0825 0.3989 1.0000 3.250 0.8596 0.01570 0.00752 -0.0799 0.3888 1.0000 3.500 0.8722 0.01589 0.00770 -0.0771 0.3785 1.0000 3.750 0.8863 0.01622 0.00788 -0.0746 0.3701 1.0000 4.000 0.8993 0.01642 0.00809 -0.0719 0.3618 1.0000 4.250 0.9147 0.01675 0.00829 -0.0697 0.3548 1.0000 4.500 0.9289 0.01699 0.00854 -0.0672 0.3480 1.0000 4.750 0.9434 0.01725 0.00876 -0.0648 0.3417 1.0000 5.000 0.9621 0.01764 0.00902 -0.0633 0.3360 1.0000 5.250 0.9754 0.01786 0.00930 -0.0606 0.3304 1.0000 5.500 0.9908 0.01814 0.00954 -0.0583 0.3251 1.0000 5.750 1.0131 0.01859 0.00986 -0.0575 0.3200 1.0000 6.000 1.0280 0.01886 0.01020 -0.0551 0.3159 1.0000 6.250 1.0445 0.01917 0.01053 -0.0531 0.3115 1.0000 6.500 1.0631 0.01951 0.01084 -0.0515 0.3076 1.0000 6.750 1.0887 0.02001 0.01123 -0.0514 0.3035 1.0000 7.000 1.1042 0.02035 0.01165 -0.0493 0.2999 1.0000 7.250 1.1197 0.02068 0.01204 -0.0471 0.2961 1.0000 7.500 1.1385 0.02105 0.01242 -0.0456 0.2926 1.0000 7.750 1.1597 0.02147 0.01280 -0.0446 0.2891 1.0000 8.000 1.1853 0.02204 0.01333 -0.0446 0.2853 1.0000 8.250 1.1937 0.02233 0.01373 -0.0411 0.2817 1.0000 8.500 1.2054 0.02263 0.01408 -0.0383 0.2779 1.0000 8.750 1.2214 0.02297 0.01441 -0.0363 0.2742 1.0000 9.000 1.2532 0.02364 0.01496 -0.0376 0.2699 1.0000 9.250 1.2566 0.02391 0.01538 -0.0332 0.2670 1.0000 9.500 1.2662 0.02427 0.01584 -0.0302 0.2637 1.0000 9.750 1.2800 0.02466 0.01627 -0.0280 0.2603 1.0000 10.000 1.2987 0.02509 0.01670 -0.0267 0.2572 1.0000 10.250 1.3314 0.02584 0.01736 -0.0282 0.2535 1.0000 10.500 1.3351 0.02626 0.01796 -0.0243 0.2511 1.0000 10.750 1.3440 0.02676 0.01859 -0.0214 0.2481 1.0000 11.000 1.3564 0.02725 0.01915 -0.0192 0.2450 1.0000 11.250 1.3726 0.02772 0.01965 -0.0177 0.2419 1.0000 11.500 1.3983 0.02832 0.02018 -0.0179 0.2386 1.0000 11.750 1.4063 0.02902 0.02102 -0.0152 0.2357 1.0000 12.000 1.4098 0.02966 0.02182 -0.0119 0.2326 1.0000 12.250 1.4178 0.03023 0.02249 -0.0094 0.2291 1.0000 12.500 1.4318 0.03072 0.02298 -0.0078 0.2256 1.0000 12.750 1.4575 0.03139 0.02358 -0.0081 0.2218 1.0000 13.000 1.4521 0.03228 0.02470 -0.0040 0.2191 1.0000 13.250 1.4535 0.03316 0.02574 -0.0010 0.2156 1.0000 13.500 1.4615 0.03387 0.02651 0.0010 0.2120 1.0000 13.750 1.4786 0.03438 0.02694 0.0019 0.2082 1.0000 14.000 1.4790 0.03557 0.02828 0.0044 0.2047 1.0000 14.250 1.4734 0.03687 0.02976 0.0074 0.2009 1.0000 14.500 1.4769 0.03783 0.03079 0.0094 0.1969 1.0000 14.750 1.4941 0.03835 0.03117 0.0100 0.1924 1.0000 15.000 1.4809 0.04036 0.03345 0.0128 0.1890 1.0000 15.250 1.4761 0.04212 0.03536 0.0147 0.1850 1.0000 15.500 1.4789 0.04341 0.03667 0.0159 0.1810 1.0000 15.750 1.4830 0.04483 0.03809 0.0170 0.1769 1.0000 16.000 1.4715 0.04757 0.04105 0.0183 0.1730 1.0000 16.250 1.4691 0.04972 0.04331 0.0190 0.1693 1.0000 16.500 1.4747 0.05124 0.04479 0.0195 0.1656 1.0000 16.750 1.4677 0.05414 0.04784 0.0199 0.1621 1.0000 17.000 1.4584 0.05743 0.05131 0.0201 0.1587 1.0000 17.250 1.4553 0.06015 0.05409 0.0200 0.1552 1.0000 17.500 1.4635 0.06162 0.05549 0.0201 0.1519 1.0000 17.750 1.4488 0.06594 0.06002 0.0196 0.1490 1.0000 18.000 1.4356 0.07025 0.06451 0.0188 0.1461 1.0000 18.250 1.4293 0.07378 0.06814 0.0180 0.1433 1.0000 18.500 1.4330 0.07600 0.07035 0.0176 0.1404 1.0000 18.750 1.4263 0.07967 0.07409 0.0167 0.1377 1.0000 19.000 1.4037 0.08575 0.08039 0.0148 0.1355 1.0000 19.250 1.3843 0.09151 0.08631 0.0128 0.1330 1.0000