XFOIL Version 6.96 Calculated polar for: GOE 646 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.750 -0.8802 0.09161 0.08823 -0.0794 1.0000 0.0342 -18.500 -0.8848 0.08808 0.08467 -0.0808 1.0000 0.0345 -18.250 -0.8920 0.08425 0.08079 -0.0823 1.0000 0.0347 -18.000 -0.8969 0.08079 0.07729 -0.0836 1.0000 0.0351 -17.750 -0.9051 0.07701 0.07346 -0.0850 1.0000 0.0352 -17.500 -0.9117 0.07351 0.06991 -0.0861 1.0000 0.0356 -17.250 -0.9217 0.06964 0.06597 -0.0875 1.0000 0.0359 -17.000 -0.9293 0.06626 0.06255 -0.0884 1.0000 0.0361 -16.750 -0.9411 0.06253 0.05876 -0.0894 1.0000 0.0363 -16.500 -0.9560 0.05879 0.05495 -0.0901 1.0000 0.0364 -16.250 -0.9713 0.05536 0.05146 -0.0904 1.0000 0.0366 -16.000 -0.9804 0.05034 0.04636 -0.0949 0.9989 0.0369 -15.750 -0.9854 0.04497 0.04092 -0.1007 0.9968 0.0374 -15.500 -0.9858 0.03987 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0.5639 0.3145 -0.750 0.4348 0.00825 0.00227 -0.1174 0.5581 0.3203 -0.500 0.4606 0.00825 0.00229 -0.1168 0.5541 0.3268 -0.250 0.4870 0.00825 0.00230 -0.1163 0.5503 0.3321 0.000 0.5130 0.00829 0.00232 -0.1158 0.5460 0.3361 0.250 0.5373 0.00831 0.00234 -0.1149 0.5413 0.3433 0.500 0.5609 0.00836 0.00239 -0.1139 0.5362 0.3494 0.750 0.5865 0.00836 0.00241 -0.1132 0.5329 0.3546 1.000 0.6112 0.00837 0.00243 -0.1124 0.5290 0.3607 1.250 0.6347 0.00838 0.00246 -0.1114 0.5249 0.3679 1.500 0.6575 0.00844 0.00250 -0.1102 0.5204 0.3744 1.750 0.6810 0.00848 0.00255 -0.1092 0.5158 0.3814 2.000 0.7057 0.00847 0.00259 -0.1084 0.5116 0.3905 2.250 0.7291 0.00851 0.00263 -0.1073 0.5058 0.3975 2.500 0.7506 0.00858 0.00270 -0.1059 0.5000 0.4070 2.750 0.7743 0.00862 0.00276 -0.1050 0.4945 0.4168 3.000 0.7974 0.00865 0.00283 -0.1039 0.4883 0.4282 3.250 0.8186 0.00874 0.00292 -0.1024 0.4819 0.4406 3.500 0.8412 0.00878 0.00302 -0.1013 0.4766 0.4582 3.750 0.8645 0.00880 0.00312 -0.1003 0.4709 0.4821 4.000 0.8853 0.00886 0.00324 -0.0988 0.4641 0.5132 4.250 0.9065 0.00890 0.00338 -0.0974 0.4575 0.5508 4.500 0.9277 0.00896 0.00352 -0.0960 0.4494 0.5870 4.750 0.9464 0.00909 0.00369 -0.0942 0.4403 0.6170 5.000 0.9668 0.00920 0.00383 -0.0926 0.4293 0.6401 5.250 0.9856 0.00937 0.00400 -0.0909 0.4167 0.6592 5.500 1.0026 0.00960 0.00420 -0.0887 0.4016 0.6759 5.750 1.0176 0.00988 0.00443 -0.0863 0.3837 0.6923 6.000 1.0310 0.01020 0.00471 -0.0836 0.3636 0.7101 6.250 1.0445 0.01051 0.00501 -0.0810 0.3478 0.7314 6.500 1.0562 0.01077 0.00533 -0.0780 0.3352 0.7713 6.750 1.1349 0.01100 0.00589 -0.0894 0.3169 1.0000 7.000 1.1555 0.01127 0.00614 -0.0882 0.3099 1.0000 7.250 1.1736 0.01165 0.00646 -0.0866 0.3017 1.0000 7.500 1.1942 0.01194 0.00674 -0.0855 0.2959 1.0000 7.750 1.2144 0.01226 0.00705 -0.0843 0.2901 1.0000 8.000 1.2324 0.01269 0.00742 -0.0828 0.2830 1.0000 8.250 1.2534 0.01299 0.00773 -0.0819 0.2780 1.0000 8.500 1.2724 0.01340 0.00811 -0.0806 0.2705 1.0000 8.750 1.2904 0.01386 0.00853 -0.0793 0.2637 1.0000 9.000 1.3111 0.01421 0.00889 -0.0784 0.2584 1.0000 9.250 1.3292 0.01469 0.00934 -0.0772 0.2518 1.0000 9.500 1.3474 0.01518 0.00982 -0.0760 0.2460 1.0000 9.750 1.3664 0.01563 0.01027 -0.0749 0.2398 1.0000 10.000 1.3820 0.01627 0.01087 -0.0735 0.2317 1.0000 10.250 1.4004 0.01677 0.01137 -0.0725 0.2259 1.0000 10.500 1.4160 0.01743 0.01200 -0.0711 0.2187 1.0000 10.750 1.4317 0.01809 0.01265 -0.0698 0.2117 1.0000 11.000 1.4460 0.01885 0.01338 -0.0684 0.2038 1.0000 11.250 1.4606 0.01961 0.01413 -0.0671 0.1976 1.0000 11.500 1.4746 0.02041 0.01491 -0.0658 0.1913 1.0000 11.750 1.4863 0.02136 0.01584 -0.0642 0.1844 1.0000 12.000 1.5001 0.02222 0.01670 -0.0630 0.1789 1.0000 12.250 1.5098 0.02335 0.01780 -0.0614 0.1717 1.0000 12.500 1.5228 0.02428 0.01875 -0.0602 0.1672 1.0000 12.750 1.5331 0.02542 0.01988 -0.0588 0.1613 1.0000 13.000 1.5428 0.02663 0.02109 -0.0575 0.1561 1.0000 13.250 1.5544 0.02774 0.02221 -0.0563 0.1511 1.0000 13.500 1.5606 0.02926 0.02371 -0.0549 0.1447 1.0000 13.750 1.5709 0.03051 0.02499 -0.0538 0.1393 1.0000 14.000 1.5752 0.03225 0.02670 -0.0523 0.1311 1.0000 14.250 1.5780 0.03419 0.02859 -0.0510 0.1205 1.0000 14.500 1.5747 0.03666 0.03100 -0.0494 0.1049 1.0000 15.000 1.5622 0.04244 0.03667 -0.0465 0.0835 1.0000 15.250 1.5628 0.04487 0.03912 -0.0456 0.0797 1.0000 15.500 1.5635 0.04730 0.04158 -0.0448 0.0772 1.0000 15.750 1.5622 0.05000 0.04430 -0.0441 0.0745 1.0000 16.000 1.5650 0.05234 0.04669 -0.0435 0.0730 1.0000 16.250 1.5678 0.05470 0.04912 -0.0431 0.0717 1.0000 16.500 1.5699 0.05713 0.05160 -0.0426 0.0705 1.0000 16.750 1.5682 0.06002 0.05454 -0.0422 0.0689 1.0000 17.000 1.5658 0.06304 0.05761 -0.0419 0.0678 1.0000 17.250 1.5606 0.06639 0.06101 -0.0417 0.0664 1.0000 17.500 1.5633 0.06889 0.06358 -0.0415 0.0657 1.0000 17.750 1.5653 0.07148 0.06624 -0.0414 0.0650 1.0000 18.000 1.5659 0.07426 0.06908 -0.0414 0.0640 1.0000 18.250 1.5642 0.07734 0.07222 -0.0414 0.0631 1.0000 18.500 1.5621 0.08048 0.07541 -0.0415 0.0622 1.0000 18.750 1.5568 0.08404 0.07903 -0.0417 0.0615 1.0000 19.000 1.5497 0.08785 0.08290 -0.0420 0.0603 1.0000