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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.000 -0.9069 0.08445 0.08112 -0.0841 1.0000 0.0381 -18.750 -0.9308 0.07783 0.07442 -0.0881 1.0000 0.0383 -18.500 -0.9618 0.07063 0.06711 -0.0926 1.0000 0.0385 -18.250 -0.9975 0.06293 0.05929 -0.0973 1.0000 0.0386 -18.000 -1.0346 0.05503 0.05124 -0.1023 1.0000 0.0387 -17.750 -1.0674 0.04746 0.04353 -0.1073 1.0000 0.0389 -17.500 -1.0822 0.04093 0.03685 -0.1133 0.9916 0.0390 -17.000 -1.0811 0.03209 0.02773 -0.1227 0.9607 0.0395 -16.750 -1.0786 0.02938 0.02489 -0.1244 0.9431 0.0397 -16.500 -1.0744 0.02736 0.02273 -0.1250 0.9280 0.0399 -16.250 -1.0672 0.02577 0.02103 -0.1250 0.9157 0.0401 -16.000 -1.0580 0.02451 0.01965 -0.1246 0.9052 0.0403 -15.750 -1.0470 0.02346 0.01850 -0.1239 0.8946 0.0406 -15.500 -1.0346 0.02258 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0.4645 0.0750 -1.000 0.4529 0.01050 0.00313 -0.1012 0.4606 0.0761 -0.750 0.4810 0.01049 0.00310 -0.1011 0.4560 0.0771 -0.500 0.5085 0.01047 0.00307 -0.1010 0.4516 0.0788 -0.250 0.5364 0.01044 0.00305 -0.1009 0.4479 0.0807 0.000 0.5646 0.01042 0.00303 -0.1008 0.4437 0.0827 0.250 0.5923 0.01041 0.00302 -0.1007 0.4381 0.0857 0.750 0.6460 0.01026 0.00302 -0.1003 0.4257 0.1430 1.000 0.6725 0.01030 0.00307 -0.1000 0.4158 0.1568 1.250 0.6988 0.01037 0.00313 -0.0996 0.4036 0.1680 1.500 0.7236 0.01052 0.00322 -0.0991 0.3859 0.1766 1.750 0.7473 0.01074 0.00335 -0.0983 0.3666 0.1837 2.000 0.7713 0.01093 0.00349 -0.0976 0.3511 0.1927 2.250 0.7956 0.01111 0.00364 -0.0970 0.3394 0.2021 2.500 0.8198 0.01127 0.00379 -0.0963 0.3295 0.2158 2.750 0.8448 0.01138 0.00392 -0.0958 0.3229 0.2320 3.000 0.8696 0.01148 0.00405 -0.0953 0.3170 0.2519 3.250 0.8936 0.01161 0.00422 -0.0947 0.3110 0.2780 3.500 0.9185 0.01165 0.00436 -0.0942 0.3070 0.3153 3.750 0.9428 0.01169 0.00452 -0.0936 0.3031 0.3609 4.000 0.9655 0.01176 0.00468 -0.0928 0.2992 0.4051 4.250 0.9872 0.01183 0.00487 -0.0918 0.2954 0.4549 4.500 1.0092 0.01188 0.00507 -0.0908 0.2919 0.5190 4.750 1.0338 0.01183 0.00527 -0.0904 0.2901 0.6101 5.000 1.0579 0.01178 0.00550 -0.0899 0.2878 0.7128 5.250 1.0799 0.01174 0.00576 -0.0889 0.2850 0.8197 5.500 1.0967 0.01176 0.00605 -0.0865 0.2821 0.9244 5.750 1.1282 0.01200 0.00631 -0.0875 0.2784 1.0000 6.000 1.1490 0.01228 0.00657 -0.0865 0.2752 1.0000 6.250 1.1717 0.01250 0.00679 -0.0857 0.2736 1.0000 6.500 1.1947 0.01273 0.00701 -0.0850 0.2719 1.0000 6.750 1.2171 0.01298 0.00726 -0.0843 0.2699 1.0000 7.000 1.2390 0.01326 0.00753 -0.0835 0.2676 1.0000 7.250 1.2604 0.01357 0.00783 -0.0827 0.2652 1.0000 7.500 1.2811 0.01392 0.00817 -0.0818 0.2628 1.0000 7.750 1.3012 0.01431 0.00855 -0.0809 0.2602 1.0000 8.000 1.3212 0.01471 0.00894 -0.0800 0.2577 1.0000 8.250 1.3429 0.01504 0.00928 -0.0793 0.2564 1.0000 8.500 1.3644 0.01539 0.00964 -0.0787 0.2547 1.0000 8.750 1.3852 0.01578 0.01004 -0.0780 0.2528 1.0000 9.000 1.4050 0.01622 0.01049 -0.0772 0.2507 1.0000 9.250 1.4245 0.01669 0.01096 -0.0764 0.2487 1.0000 9.500 1.4431 0.01721 0.01149 -0.0755 0.2468 1.0000 9.750 1.4607 0.01780 0.01208 -0.0745 0.2447 1.0000 10.000 1.4776 0.01844 0.01272 -0.0735 0.2421 1.0000 10.250 1.4967 0.01898 0.01328 -0.0728 0.2406 1.0000 10.500 1.5156 0.01953 0.01386 -0.0721 0.2388 1.0000 10.750 1.5335 0.02014 0.01449 -0.0714 0.2371 1.0000 11.000 1.5502 0.02084 0.01521 -0.0705 0.2350 1.0000 11.250 1.5660 0.02161 0.01599 -0.0696 0.2324 1.0000 11.500 1.5796 0.02254 0.01693 -0.0686 0.2298 1.0000 11.750 1.5932 0.02349 0.01789 -0.0676 0.2275 1.0000 12.000 1.6079 0.02439 0.01882 -0.0668 0.2260 1.0000 12.250 1.6237 0.02523 0.01970 -0.0661 0.2245 1.0000 12.500 1.6379 0.02621 0.02071 -0.0653 0.2228 1.0000 12.750 1.6518 0.02723 0.02177 -0.0646 0.2207 1.0000 13.000 1.6629 0.02850 0.02305 -0.0638 0.2180 1.0000 13.250 1.6720 0.02994 0.02451 -0.0628 0.2149 1.0000 13.500 1.6807 0.03146 0.02605 -0.0620 0.2118 1.0000 13.750 1.6920 0.03282 0.02745 -0.0613 0.2091 1.0000 14.000 1.7017 0.03432 0.02898 -0.0607 0.2059 1.0000 14.250 1.7081 0.03615 0.03083 -0.0599 0.2024 1.0000 14.500 1.7112 0.03831 0.03301 -0.0591 0.1988 1.0000 14.750 1.7194 0.04003 0.03477 -0.0586 0.1957 1.0000 15.000 1.7251 0.04199 0.03676 -0.0580 0.1918 1.0000 15.250 1.7254 0.04450 0.03929 -0.0573 0.1875 1.0000 15.500 1.7276 0.04684 0.04165 -0.0566 0.1836 1.0000 15.750 1.7297 0.04916 0.04399 -0.0560 0.1787 1.0000 16.000 1.7245 0.05225 0.04710 -0.0553 0.1736 1.0000 16.250 1.7260 0.05469 0.04957 -0.0548 0.1690 1.0000 16.500 1.7213 0.05776 0.05265 -0.0542 0.1635 1.0000 16.750 1.7169 0.06084 0.05575 -0.0537 0.1583 1.0000 17.000 1.7112 0.06406 0.05898 -0.0532 0.1521 1.0000 17.250 1.7039 0.06756 0.06250 -0.0528 0.1465 1.0000 17.500 1.6970 0.07097 0.06591 -0.0525 0.1408 1.0000 17.750 1.6899 0.07451 0.06948 -0.0523 0.1363 1.0000 18.000 1.6843 0.07788 0.07287 -0.0521 0.1318 1.0000 18.250 1.6765 0.08159 0.07662 -0.0520 0.1283 1.0000 18.500 1.6750 0.08456 0.07963 -0.0521 0.1255 1.0000 18.750 1.6684 0.08818 0.08330 -0.0521 0.1229 1.0000 19.000 1.6630 0.09167 0.08682 -0.0523 0.1203 1.0000