XFOIL Version 6.96 Calculated polar for: GOE 386 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 -0.8856 0.08149 0.07830 -0.0874 1.0000 0.0426 -18.500 -0.9125 0.07415 0.07082 -0.0923 1.0000 0.0427 -18.250 -0.9377 0.06748 0.06402 -0.0967 1.0000 0.0429 -18.000 -0.9607 0.06163 0.05807 -0.1002 1.0000 0.0432 -17.750 -0.9760 0.05665 0.05301 -0.1033 1.0000 0.0434 -17.500 -0.9883 0.05192 0.04822 -0.1063 1.0000 0.0436 -17.250 -0.9977 0.04753 0.04375 -0.1092 1.0000 0.0438 -17.000 -1.0046 0.04347 0.03962 -0.1119 1.0000 0.0440 -16.750 -1.0107 0.03988 0.03596 -0.1140 1.0000 0.0442 -16.500 -1.0143 0.03674 0.03275 -0.1159 0.9990 0.0444 -16.250 -0.9970 0.03394 0.02988 -0.1202 0.9952 0.0447 -16.000 -0.9776 0.03158 0.02746 -0.1241 0.9913 0.0451 -15.750 -0.9612 0.02959 0.02539 -0.1267 0.9827 0.0454 -15.500 -0.9452 0.02789 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0.5001 0.0880 -1.000 0.4542 0.01028 0.00317 -0.1016 0.4969 0.0908 -0.750 0.4815 0.01024 0.00313 -0.1014 0.4931 0.0969 -0.500 0.5087 0.00996 0.00310 -0.1013 0.4911 0.1521 -0.250 0.5374 0.00988 0.00310 -0.1013 0.4887 0.1700 0.000 0.5659 0.00983 0.00310 -0.1014 0.4856 0.1828 0.250 0.5941 0.00981 0.00310 -0.1013 0.4820 0.1930 0.500 0.6217 0.00981 0.00311 -0.1012 0.4781 0.2037 0.750 0.6487 0.00984 0.00316 -0.1010 0.4736 0.2156 1.000 0.6774 0.00980 0.00317 -0.1010 0.4709 0.2280 1.250 0.7057 0.00975 0.00319 -0.1011 0.4674 0.2455 1.500 0.7334 0.00971 0.00321 -0.1010 0.4629 0.2677 1.750 0.7601 0.00968 0.00326 -0.1008 0.4579 0.2996 2.000 0.7869 0.00963 0.00332 -0.1006 0.4530 0.3399 2.250 0.8145 0.00954 0.00337 -0.1006 0.4475 0.3874 2.500 0.8405 0.00948 0.00343 -0.1002 0.4400 0.4444 2.750 0.8660 0.00936 0.00352 -0.0999 0.4325 0.5270 3.000 0.8905 0.00918 0.00363 -0.0994 0.4225 0.6425 3.250 0.9127 0.00900 0.00379 -0.0982 0.4114 0.7752 3.500 0.9318 0.00899 0.00399 -0.0963 0.3965 0.8764 3.750 0.9510 0.00918 0.00422 -0.0944 0.3787 0.9404 4.000 0.9808 0.00954 0.00448 -0.0949 0.3603 0.9765 4.250 1.0185 0.00993 0.00476 -0.0972 0.3454 0.9936 4.500 1.0520 0.01027 0.00502 -0.0987 0.3348 1.0000 4.750 1.0675 0.01049 0.00518 -0.0964 0.3280 1.0000 5.000 1.0839 0.01070 0.00535 -0.0942 0.3226 1.0000 5.250 1.1006 0.01097 0.00558 -0.0921 0.3173 1.0000 5.500 1.1201 0.01122 0.00580 -0.0907 0.3129 1.0000 5.750 1.1419 0.01142 0.00599 -0.0897 0.3100 1.0000 6.000 1.1631 0.01167 0.00622 -0.0886 0.3064 1.0000 6.250 1.1831 0.01198 0.00650 -0.0874 0.3025 1.0000 6.500 1.2013 0.01238 0.00685 -0.0859 0.2977 1.0000 6.750 1.2242 0.01261 0.00709 -0.0853 0.2954 1.0000 7.000 1.2469 0.01286 0.00734 -0.0846 0.2931 1.0000 7.250 1.2686 0.01315 0.00763 -0.0838 0.2906 1.0000 7.500 1.2894 0.01348 0.00796 -0.0829 0.2882 1.0000 7.750 1.3090 0.01389 0.00834 -0.0818 0.2855 1.0000 8.000 1.3270 0.01437 0.00880 -0.0806 0.2822 1.0000 8.250 1.3460 0.01481 0.00925 -0.0796 0.2797 1.0000 8.500 1.3682 0.01512 0.00958 -0.0790 0.2785 1.0000 8.750 1.3900 0.01546 0.00994 -0.0784 0.2768 1.0000 9.000 1.4108 0.01585 0.01034 -0.0777 0.2749 1.0000 9.250 1.4304 0.01630 0.01080 -0.0769 0.2727 1.0000 9.500 1.4490 0.01682 0.01131 -0.0760 0.2703 1.0000 9.750 1.4653 0.01746 0.01195 -0.0748 0.2677 1.0000 10.000 1.4797 0.01822 0.01270 -0.0735 0.2647 1.0000 10.250 1.4988 0.01875 0.01326 -0.0728 0.2632 1.0000 10.500 1.5192 0.01921 0.01375 -0.0722 0.2617 1.0000 10.750 1.5389 0.01971 0.01429 -0.0717 0.2599 1.0000 11.000 1.5567 0.02034 0.01493 -0.0709 0.2579 1.0000 11.250 1.5734 0.02103 0.01564 -0.0701 0.2558 1.0000 11.500 1.5885 0.02185 0.01647 -0.0691 0.2538 1.0000 11.750 1.6016 0.02281 0.01744 -0.0680 0.2516 1.0000 12.000 1.6117 0.02396 0.01859 -0.0667 0.2490 1.0000 12.250 1.6278 0.02476 0.01943 -0.0660 0.2476 1.0000 12.500 1.6450 0.02551 0.02024 -0.0654 0.2464 1.0000 12.750 1.6607 0.02638 0.02115 -0.0648 0.2448 1.0000 13.000 1.6762 0.02728 0.02209 -0.0642 0.2430 1.0000 13.250 1.6890 0.02840 0.02324 -0.0635 0.2410 1.0000 13.500 1.7004 0.02964 0.02450 -0.0627 0.2386 1.0000 13.750 1.7079 0.03123 0.02610 -0.0617 0.2358 1.0000 14.000 1.7151 0.03288 0.02776 -0.0608 0.2331 1.0000 14.250 1.7303 0.03391 0.02886 -0.0604 0.2316 1.0000 14.500 1.7431 0.03518 0.03018 -0.0600 0.2297 1.0000 14.750 1.7542 0.03656 0.03160 -0.0595 0.2274 1.0000 15.000 1.7618 0.03830 0.03337 -0.0589 0.2247 1.0000 15.250 1.7660 0.04037 0.03546 -0.0582 0.2217 1.0000 15.500 1.7698 0.04247 0.03759 -0.0575 0.2187 1.0000 15.750 1.7808 0.04397 0.03915 -0.0572 0.2167 1.0000 16.000 1.7900 0.04559 0.04082 -0.0568 0.2141 1.0000 16.250 1.7942 0.04772 0.04298 -0.0564 0.2111 1.0000 16.500 1.7948 0.05019 0.04547 -0.0558 0.2076 1.0000 16.750 1.7964 0.05260 0.04791 -0.0553 0.2045 1.0000 17.000 1.8043 0.05437 0.04974 -0.0550 0.2015 1.0000 17.250 1.8056 0.05683 0.05223 -0.0546 0.1977 1.0000 17.500 1.8009 0.05988 0.05529 -0.0540 0.1933 1.0000 17.750 1.8031 0.06227 0.05773 -0.0537 0.1895 1.0000 18.000 1.8030 0.06490 0.06038 -0.0534 0.1845 1.0000 18.250 1.7935 0.06857 0.06406 -0.0530 0.1793 1.0000 18.500 1.7946 0.07110 0.06663 -0.0528 0.1745 1.0000 18.750 1.7841 0.07494 0.07047 -0.0526 0.1687 1.0000 19.000 1.7792 0.07819 0.07376 -0.0525 0.1635 1.0000 19.250 1.7681 0.08216 0.07774 -0.0524 0.1576 1.0000