XFOIL Version 6.96 Calculated polar for: GOE 683 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 ------ -------- --------- --------- -------- -------- -------- -17.500 -0.8015 0.08320 0.07779 -0.0730 1.0000 0.0525 -17.250 -0.8337 0.07519 0.06955 -0.0778 1.0000 0.0529 -17.000 -0.8573 0.06889 0.06303 -0.0813 1.0000 0.0533 -16.750 -0.8756 0.06364 0.05759 -0.0839 1.0000 0.0537 -16.500 -0.8927 0.05888 0.05260 -0.0860 1.0000 0.0542 -16.250 -0.9078 0.05470 0.04819 -0.0875 1.0000 0.0547 -16.000 -0.9062 0.05245 0.04591 -0.0876 1.0000 0.0551 -15.750 -0.9043 0.05035 0.04379 -0.0876 1.0000 0.0556 -15.500 -0.9035 0.04825 0.04164 -0.0875 1.0000 0.0561 -15.250 -0.9033 0.04615 0.03948 -0.0871 1.0000 0.0565 -15.000 -0.9032 0.04420 0.03746 -0.0864 1.0000 0.0570 -14.750 -0.9029 0.04238 0.03555 -0.0855 1.0000 0.0576 -14.500 -0.9023 0.04068 0.03376 -0.0843 1.0000 0.0582 -14.250 -0.9016 0.03911 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0.6326 0.000 0.2307 0.01300 0.00520 -0.0246 0.4989 0.7045 0.250 0.3543 0.01361 0.00603 -0.0439 0.4886 0.7842 0.500 0.4146 0.01419 0.00661 -0.0499 0.4820 0.8134 0.750 0.4510 0.01455 0.00695 -0.0512 0.4757 0.8342 1.000 0.4771 0.01487 0.00721 -0.0505 0.4702 0.8557 1.750 0.5550 0.01586 0.00810 -0.0486 0.4551 0.9019 2.000 0.5793 0.01616 0.00831 -0.0477 0.4502 0.9122 2.250 0.6114 0.01648 0.00859 -0.0485 0.4455 0.9205 2.500 0.6440 0.01680 0.00890 -0.0493 0.4404 0.9291 2.750 0.6708 0.01715 0.00922 -0.0490 0.4356 0.9394 3.000 0.7115 0.01741 0.00939 -0.0517 0.4309 0.9440 3.250 0.7439 0.01763 0.00959 -0.0527 0.4263 0.9498 3.500 0.7706 0.01783 0.00981 -0.0526 0.4219 0.9554 3.750 0.8054 0.01796 0.00991 -0.0542 0.4171 0.9587 4.000 0.8356 0.01815 0.01004 -0.0549 0.4128 0.9636 4.250 0.8659 0.01835 0.01023 -0.0556 0.4078 0.9690 4.500 0.9021 0.01843 0.01032 -0.0575 0.4018 0.9732 4.750 0.9301 0.01860 0.01045 -0.0578 0.3962 0.9780 5.000 0.9579 0.01877 0.01056 -0.0581 0.3924 0.9814 5.250 0.9896 0.01881 0.01066 -0.0593 0.3879 0.9841 5.500 1.0187 0.01890 0.01078 -0.0599 0.3835 0.9873 5.750 1.0460 0.01906 0.01093 -0.0602 0.3793 0.9907 6.000 1.0746 0.01919 0.01102 -0.0607 0.3755 0.9934 6.250 1.1057 0.01924 0.01112 -0.0618 0.3714 0.9964 6.500 1.1369 0.01932 0.01125 -0.0629 0.3673 0.9993 6.750 1.1561 0.01951 0.01147 -0.0616 0.3633 1.0000 7.000 1.1703 0.01977 0.01171 -0.0593 0.3597 1.0000 7.250 1.1843 0.02004 0.01196 -0.0570 0.3563 1.0000 7.500 1.1978 0.02030 0.01230 -0.0546 0.3528 1.0000 7.750 1.2102 0.02057 0.01263 -0.0520 0.3491 1.0000 8.000 1.2212 0.02086 0.01294 -0.0491 0.3454 1.0000 8.250 1.2313 0.02116 0.01324 -0.0462 0.3422 1.0000 8.500 1.2378 0.02146 0.01354 -0.0425 0.3386 1.0000 8.750 1.2418 0.02175 0.01392 -0.0384 0.3351 1.0000 9.000 1.2457 0.02208 0.01430 -0.0344 0.3314 1.0000 9.250 1.2503 0.02244 0.01470 -0.0306 0.3281 1.0000 9.500 1.2550 0.02284 0.01511 -0.0269 0.3249 1.0000 9.750 1.2602 0.02329 0.01556 -0.0234 0.3216 1.0000 10.000 1.2649 0.02379 0.01616 -0.0201 0.3179 1.0000 10.250 1.2702 0.02433 0.01678 -0.0169 0.3145 1.0000 10.500 1.2750 0.02493 0.01741 -0.0138 0.3110 1.0000 10.750 1.2795 0.02558 0.01807 -0.0108 0.3075 1.0000 11.000 1.2848 0.02627 0.01881 -0.0081 0.3042 1.0000 11.250 1.2887 0.02708 0.01971 -0.0053 0.3002 1.0000 11.500 1.2913 0.02797 0.02065 -0.0025 0.2955 1.0000 11.750 1.2942 0.02889 0.02158 0.0001 0.2913 1.0000 12.000 1.2963 0.02995 0.02270 0.0026 0.2865 1.0000 12.250 1.2983 0.03110 0.02393 0.0049 0.2818 1.0000 12.500 1.2998 0.03232 0.02518 0.0072 0.2770 1.0000 12.750 1.3012 0.03358 0.02646 0.0093 0.2723 1.0000 13.000 1.3020 0.03504 0.02802 0.0113 0.2673 1.0000 13.250 1.3017 0.03660 0.02964 0.0132 0.2621 1.0000 13.500 1.3003 0.03826 0.03128 0.0150 0.2568 1.0000 13.750 1.2991 0.04010 0.03324 0.0166 0.2513 1.0000 14.000 1.2951 0.04218 0.03535 0.0181 0.2447 1.0000 14.250 1.2921 0.04427 0.03749 0.0195 0.2391 1.0000 14.500 1.2880 0.04661 0.03991 0.0207 0.2326 1.0000 14.750 1.2809 0.04922 0.04251 0.0219 0.2256 1.0000 15.000 1.2753 0.05192 0.04530 0.0228 0.2183 1.0000 15.250 1.2650 0.05508 0.04846 0.0236 0.2101 1.0000 15.500 1.2565 0.05825 0.05170 0.0242 0.2015 1.0000 15.750 1.2447 0.06184 0.05530 0.0247 0.1926 1.0000 16.000 1.2326 0.06558 0.05906 0.0250 0.1834 1.0000 16.250 1.2204 0.06944 0.06294 0.0251 0.1741 1.0000 16.500 1.2072 0.07349 0.06699 0.0251 0.1660 1.0000 16.750 1.1961 0.07739 0.07090 0.0250 0.1586 1.0000 17.000 1.1856 0.08128 0.07479 0.0249 0.1531 1.0000 17.250 1.1774 0.08493 0.07845 0.0247 0.1479 1.0000 17.500 1.1705 0.08841 0.08193 0.0245 0.1438 1.0000 17.750 1.1664 0.09160 0.08514 0.0243 0.1403 1.0000