XFOIL Version 6.96 Calculated polar for: GOE 12K 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 ------ -------- --------- --------- -------- -------- -------- -10.500 -0.3156 0.09408 0.09006 -0.0912 0.9530 0.0288 -10.250 -0.3177 0.09000 0.08598 -0.0930 0.9502 0.0298 -9.750 -0.3415 0.07554 0.07156 -0.1036 0.9455 0.0320 -9.250 -0.5318 0.04107 0.03638 -0.1088 0.9213 0.0334 -9.000 -0.4882 0.04444 0.03994 -0.1098 0.9209 0.0341 -8.750 -0.4551 0.04607 0.04159 -0.1104 0.9201 0.0351 -8.500 -0.4619 0.04321 0.03853 -0.1070 0.9150 0.0362 -8.250 -0.4745 0.03854 0.03341 -0.1030 0.9095 0.0383 -8.000 -0.4816 0.03257 0.02648 -0.0998 0.9063 0.0421 -7.750 -0.4545 0.03256 0.02653 -0.1002 0.9053 0.0432 -7.500 -0.4281 0.03227 0.02619 -0.1005 0.9043 0.0447 -7.250 -0.4307 0.03207 0.02589 -0.0949 0.8976 0.0457 -7.000 -0.4143 0.03114 0.02476 -0.0933 0.8946 0.0478 -6.750 -0.3961 0.02972 0.02297 -0.0919 0.8925 0.0503 -6.500 -0.3741 0.02873 0.02160 -0.0911 0.8910 0.0521 -6.250 -0.3528 0.02712 0.01975 -0.0906 0.8898 0.0539 -6.000 -0.3266 0.02639 0.01895 -0.0907 0.8889 0.0555 -5.750 -0.3289 0.02641 0.01892 -0.0849 0.8817 0.0564 -5.500 -0.3085 0.02576 0.01811 -0.0837 0.8790 0.0578 -5.250 -0.2845 0.02511 0.01730 -0.0831 0.8771 0.0594 -5.000 -0.2590 0.02439 0.01639 -0.0828 0.8757 0.0610 -4.750 -0.2322 0.02367 0.01548 -0.0827 0.8746 0.0621 -4.500 -0.2043 0.02300 0.01463 -0.0828 0.8737 0.0632 -4.250 -0.1971 0.02300 0.01452 -0.0787 0.8684 0.0640 -4.000 -0.1808 0.02284 0.01424 -0.0765 0.8644 0.0648 -3.750 -0.1564 0.02236 0.01365 -0.0759 0.8623 0.0655 -3.500 -0.1301 0.02159 0.01281 -0.0757 0.8608 0.0667 -3.250 -0.1023 0.02104 0.01221 -0.0758 0.8596 0.0676 -3.000 -0.0737 0.02058 0.01172 -0.0760 0.8586 0.0685 -2.750 -0.0450 0.02017 0.01129 -0.0762 0.8577 0.0696 -2.500 -0.0471 0.02052 0.01163 -0.0704 0.8500 0.0701 -2.250 -0.0252 0.02035 0.01144 -0.0693 0.8474 0.0714 -2.000 -0.0001 0.02014 0.01123 -0.0688 0.8456 0.0732 -1.750 0.0266 0.01990 0.01097 -0.0686 0.8443 0.0747 -1.500 0.0545 0.01965 0.01070 -0.0686 0.8432 0.0761 -1.250 0.0841 0.01936 0.01038 -0.0689 0.8422 0.0775 -1.000 0.0819 0.01980 0.01081 -0.0631 0.8336 0.0785 -0.750 0.1080 0.01957 0.01057 -0.0627 0.8311 0.0799 -0.500 0.1371 0.01925 0.01026 -0.0629 0.8293 0.0823 -0.250 0.1672 0.01896 0.01000 -0.0632 0.8280 0.0861 0.500 0.2224 0.01907 0.01024 -0.0578 0.8157 0.1075 0.750 0.2507 0.01878 0.01013 -0.0578 0.8141 0.1524 1.000 0.2801 0.01831 0.00997 -0.0582 0.8128 0.2297 1.250 0.2819 0.01816 0.01057 -0.0536 0.8058 0.4463 1.750 0.5763 0.01622 0.01013 -0.1056 0.8258 1.0000 2.250 0.5999 0.01678 0.01068 -0.0993 0.8137 1.0000 2.500 0.6322 0.01655 0.01045 -0.1000 0.8123 1.0000 3.000 0.6596 0.01703 0.01097 -0.0944 0.7999 1.0000 3.250 0.6963 0.01645 0.01041 -0.0957 0.7975 1.0000 3.500 0.7026 0.01669 0.01067 -0.0913 0.7862 1.0000 3.750 0.7230 0.01642 0.01042 -0.0894 0.7765 1.0000 4.000 0.7447 0.01582 0.00981 -0.0873 0.7587 1.0000 4.250 0.7785 0.01490 0.00885 -0.0874 0.7339 1.0000 4.500 0.8224 0.01402 0.00786 -0.0897 0.6975 1.0000 4.750 0.8723 0.01339 0.00691 -0.0934 0.6140 1.0000 5.000 0.8636 0.01443 0.00710 -0.0858 0.4871 1.0000 5.250 0.8633 0.01527 0.00767 -0.0804 0.4443 1.0000 5.500 0.8714 0.01591 0.00818 -0.0768 0.4170 1.0000 5.750 0.8812 0.01653 0.00868 -0.0735 0.3896 1.0000 6.000 0.8927 0.01710 0.00916 -0.0706 0.3603 1.0000 6.250 0.9020 0.01778 0.00968 -0.0674 0.3190 1.0000 6.500 0.9079 0.01867 0.01030 -0.0637 0.2632 1.0000 6.750 0.9144 0.01965 0.01097 -0.0603 0.2099 1.0000 7.000 0.9245 0.02051 0.01162 -0.0576 0.1707 1.0000 7.250 0.9372 0.02128 0.01225 -0.0553 0.1434 1.0000 7.500 0.9508 0.02200 0.01288 -0.0532 0.1251 1.0000 7.750 0.9656 0.02265 0.01350 -0.0512 0.1134 1.0000 8.000 0.9802 0.02333 0.01416 -0.0493 0.1056 1.0000 8.250 0.9958 0.02395 0.01481 -0.0475 0.0998 1.0000 8.500 1.0098 0.02468 0.01552 -0.0456 0.0946 1.0000 8.750 1.0255 0.02531 0.01621 -0.0439 0.0896 1.0000 9.000 1.0409 0.02597 0.01690 -0.0422 0.0848 1.0000 9.250 1.0538 0.02681 0.01770 -0.0402 0.0802 1.0000 9.500 1.0704 0.02739 0.01839 -0.0388 0.0766 1.0000 9.750 1.0857 0.02807 0.01912 -0.0372 0.0722 1.0000 10.000 1.0983 0.02895 0.01999 -0.0353 0.0688 1.0000 10.250 1.1145 0.02958 0.02074 -0.0338 0.0654 1.0000 10.500 1.1296 0.03029 0.02151 -0.0323 0.0613 1.0000 10.750 1.1416 0.03122 0.02244 -0.0305 0.0575 1.0000 11.000 1.1578 0.03186 0.02323 -0.0291 0.0532 1.0000 11.250 1.1715 0.03267 0.02408 -0.0276 0.0488 1.0000 11.500 1.1853 0.03350 0.02500 -0.0260 0.0445 1.0000 11.750 1.1986 0.03436 0.02594 -0.0244 0.0401 1.0000 12.000 1.2098 0.03539 0.02699 -0.0227 0.0364 1.0000 12.250 1.2216 0.03641 0.02812 -0.0210 0.0331 1.0000 12.500 1.2316 0.03757 0.02931 -0.0193 0.0305 1.0000 12.750 1.2397 0.03891 0.03068 -0.0174 0.0282 1.0000 13.000 1.2480 0.04025 0.03215 -0.0155 0.0264 1.0000 13.250 1.2559 0.04163 0.03363 -0.0137 0.0249 1.0000 13.500 1.2615 0.04322 0.03531 -0.0118 0.0237 1.0000 13.750 1.2649 0.04504 0.03721 -0.0099 0.0223 1.0000 14.000 1.2700 0.04675 0.03907 -0.0081 0.0215 1.0000 14.250 1.2739 0.04860 0.04106 -0.0064 0.0207 1.0000 14.500 1.2773 0.05049 0.04308 -0.0048 0.0198 1.0000 14.750 1.2789 0.05261 0.04530 -0.0032 0.0190 1.0000 15.000 1.2785 0.05498 0.04777 -0.0017 0.0186 1.0000 15.250 1.2750 0.05775 0.05063 -0.0003 0.0181 1.0000 15.500 1.2745 0.06031 0.05337 0.0009 0.0178 1.0000 15.750 1.2727 0.06310 0.05636 0.0020 0.0173 1.0000 16.000 1.2689 0.06620 0.05963 0.0028 0.0169 1.0000 16.250 1.2652 0.06940 0.06302 0.0033 0.0164 1.0000 16.500 1.2599 0.07288 0.06665 0.0036 0.0160 1.0000 16.750 1.2525 0.07680 0.07072 0.0035 0.0157 1.0000 17.000 1.2453 0.08085 0.07493 0.0031 0.0155 1.0000 17.250 1.2365 0.08533 0.07954 0.0022 0.0152 1.0000 17.500 1.2274 0.09004 0.08436 0.0008 0.0149 1.0000 17.750 1.2167 0.09519 0.08967 -0.0008 0.0148 1.0000 18.000 1.2048 0.10068 0.09528 -0.0028 0.0146 1.0000 18.250 1.1916 0.10663 0.10139 -0.0053 0.0145 1.0000 18.500 1.1778 0.11292 0.10787 -0.0081 0.0144 1.0000 18.750 1.1617 0.11988 0.11502 -0.0116 0.0144 1.0000 19.000 1.1457 0.12697 0.12228 -0.0153 0.0144 1.0000 19.250 1.1262 0.13518 0.13068 -0.0199 0.0143 1.0000