XFOIL Version 6.96 Calculated polar for: GOE 424 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.750 -0.7946 0.07276 0.06916 -0.0907 1.0000 0.0191 -17.500 -0.8131 0.06674 0.06302 -0.0941 1.0000 0.0193 -17.250 -0.8231 0.06227 0.05847 -0.0964 1.0000 0.0194 -17.000 -0.8305 0.05843 0.05456 -0.0983 1.0000 0.0196 -16.750 -0.8373 0.05503 0.05109 -0.0995 1.0000 0.0198 -16.500 -0.8439 0.05207 0.04806 -0.1001 1.0000 0.0199 -16.250 -0.8440 0.04921 0.04513 -0.1015 0.9988 0.0201 -16.000 -0.8346 0.04630 0.04213 -0.1045 0.9958 0.0204 -15.750 -0.8242 0.04356 0.03929 -0.1074 0.9931 0.0208 -15.500 -0.8157 0.04097 0.03659 -0.1096 0.9882 0.0212 -15.250 -0.8056 0.03842 0.03390 -0.1118 0.9838 0.0216 -15.000 -0.7968 0.03602 0.03133 -0.1134 0.9780 0.0221 -14.750 -0.7864 0.03379 0.02892 -0.1148 0.9714 0.0225 -14.500 -0.7733 0.03234 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0.3552 -0.250 0.4370 0.01110 0.00351 -0.0768 0.4871 0.4211 0.000 0.4625 0.01101 0.00353 -0.0765 0.4851 0.4639 0.250 0.4884 0.01092 0.00357 -0.0764 0.4834 0.5046 0.500 0.5145 0.01083 0.00363 -0.0762 0.4819 0.5442 0.750 0.5408 0.01077 0.00369 -0.0760 0.4801 0.5799 1.000 0.5671 0.01073 0.00375 -0.0759 0.4781 0.6102 1.250 0.5934 0.01071 0.00381 -0.0757 0.4761 0.6381 1.500 0.6195 0.01070 0.00388 -0.0755 0.4742 0.6673 1.750 0.6456 0.01070 0.00396 -0.0753 0.4723 0.6942 2.000 0.6715 0.01072 0.00404 -0.0751 0.4703 0.7183 2.250 0.6973 0.01075 0.00414 -0.0748 0.4683 0.7459 2.500 0.7230 0.01077 0.00426 -0.0745 0.4665 0.7748 2.750 0.7487 0.01078 0.00437 -0.0742 0.4646 0.8036 3.000 0.7741 0.01080 0.00450 -0.0738 0.4625 0.8302 3.250 0.7993 0.01084 0.00462 -0.0734 0.4603 0.8561 3.500 0.8244 0.01090 0.00474 -0.0729 0.4577 0.8787 3.750 0.8490 0.01098 0.00484 -0.0724 0.4545 0.8980 4.000 0.8736 0.01111 0.00495 -0.0719 0.4507 0.9151 4.250 0.9005 0.01119 0.00509 -0.0719 0.4470 0.9308 4.500 0.9295 0.01130 0.00522 -0.0724 0.4436 0.9451 4.750 0.9600 0.01143 0.00537 -0.0732 0.4408 0.9575 5.000 0.9906 0.01159 0.00552 -0.0742 0.4379 0.9687 5.250 1.0236 0.01178 0.00568 -0.0757 0.4349 0.9788 5.500 1.0600 0.01195 0.00588 -0.0779 0.4322 0.9873 5.750 1.0965 0.01211 0.00607 -0.0802 0.4292 0.9945 6.000 1.1335 0.01229 0.00627 -0.0827 0.4259 0.9996 6.250 1.1459 0.01237 0.00635 -0.0799 0.4230 1.0000 6.500 1.1588 0.01249 0.00646 -0.0773 0.4201 1.0000 6.750 1.1754 0.01264 0.00660 -0.0754 0.4171 1.0000 7.000 1.1951 0.01277 0.00678 -0.0742 0.4134 1.0000 7.250 1.2144 0.01294 0.00696 -0.0730 0.4091 1.0000 7.500 1.2329 0.01315 0.00717 -0.0717 0.4047 1.0000 7.750 1.2524 0.01338 0.00741 -0.0706 0.4002 1.0000 8.000 1.2725 0.01360 0.00766 -0.0696 0.3941 1.0000 8.250 1.2897 0.01392 0.00795 -0.0682 0.3877 1.0000 8.500 1.3094 0.01420 0.00826 -0.0673 0.3813 1.0000 8.750 1.3269 0.01456 0.00862 -0.0661 0.3742 1.0000 9.000 1.3444 0.01495 0.00901 -0.0649 0.3673 1.0000 9.250 1.3603 0.01542 0.00947 -0.0636 0.3587 1.0000 9.500 1.3754 0.01595 0.01000 -0.0622 0.3496 1.0000 9.750 1.3875 0.01663 0.01065 -0.0604 0.3397 1.0000 10.000 1.4012 0.01729 0.01130 -0.0590 0.3300 1.0000 10.250 1.4134 0.01805 0.01206 -0.0574 0.3217 1.0000 10.500 1.4237 0.01894 0.01295 -0.0557 0.3121 1.0000 10.750 1.4338 0.01991 0.01390 -0.0541 0.3023 1.0000 11.000 1.4403 0.02112 0.01509 -0.0523 0.2924 1.0000 11.250 1.4468 0.02240 0.01637 -0.0506 0.2823 1.0000 11.500 1.4527 0.02378 0.01776 -0.0490 0.2731 1.0000 12.000 1.4593 0.02715 0.02113 -0.0458 0.2547 1.0000 12.250 1.4593 0.02923 0.02321 -0.0443 0.2467 1.0000 12.500 1.4631 0.03110 0.02511 -0.0432 0.2391 1.0000 12.750 1.4614 0.03351 0.02754 -0.0419 0.2325 1.0000 13.000 1.4658 0.03549 0.02956 -0.0411 0.2269 1.0000 13.250 1.4660 0.03790 0.03201 -0.0403 0.2211 1.0000 13.500 1.4637 0.04061 0.03474 -0.0394 0.2161 1.0000 13.750 1.4669 0.04282 0.03701 -0.0388 0.2112 1.0000 14.000 1.4655 0.04551 0.03975 -0.0382 0.2058 1.0000 14.250 1.4612 0.04852 0.04278 -0.0375 0.2008 1.0000 14.500 1.4639 0.05085 0.04516 -0.0370 0.1959 1.0000 14.750 1.4618 0.05366 0.04801 -0.0365 0.1906 1.0000 15.000 1.4573 0.05676 0.05113 -0.0360 0.1858 1.0000 15.250 1.4592 0.05922 0.05365 -0.0357 0.1803 1.0000 15.500 1.4549 0.06237 0.05681 -0.0353 0.1741 1.0000 15.750 1.4531 0.06527 0.05975 -0.0351 0.1683 1.0000 16.000 1.4496 0.06837 0.06286 -0.0348 0.1609 1.0000 16.250 1.4456 0.07160 0.06611 -0.0347 0.1539 1.0000 16.500 1.4380 0.07526 0.06975 -0.0345 0.1452 1.0000 16.750 1.4313 0.07883 0.07332 -0.0344 0.1357 1.0000 17.000 1.4240 0.08252 0.07701 -0.0344 0.1277 1.0000 17.250 1.4168 0.08624 0.08072 -0.0345 0.1206 1.0000 17.500 1.4131 0.08960 0.08410 -0.0347 0.1145 1.0000 17.750 1.4065 0.09329 0.08780 -0.0349 0.1085 1.0000 18.000 1.4037 0.09658 0.09112 -0.0352 0.1030 1.0000 18.250 1.3966 0.10043 0.09497 -0.0356 0.0970 1.0000 18.500 1.3926 0.10394 0.09851 -0.0360 0.0899 1.0000 18.750 1.3858 0.10783 0.10239 -0.0366 0.0811 1.0000 19.000 1.3655 0.11353 0.10800 -0.0375 0.0619 1.0000 19.250 1.3439 0.11952 0.11392 -0.0386 0.0483 1.0000