XFOIL Version 6.96 Calculated polar for: GOE 420 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 ------ -------- --------- --------- -------- -------- -------- -19.250 -0.7466 0.10878 0.10594 -0.0740 1.0000 0.0271 -19.000 -0.7673 0.10150 0.09853 -0.0784 1.0000 0.0271 -18.750 -0.7874 0.09447 0.09137 -0.0828 1.0000 0.0272 -18.500 -0.8021 0.08867 0.08545 -0.0863 1.0000 0.0272 -18.250 -0.8190 0.08284 0.07951 -0.0896 1.0000 0.0273 -18.000 -0.8324 0.07782 0.07438 -0.0922 1.0000 0.0274 -17.750 -0.8395 0.07382 0.07030 -0.0942 1.0000 0.0275 -17.500 -0.8460 0.07002 0.06643 -0.0960 1.0000 0.0276 -17.250 -0.8490 0.06675 0.06311 -0.0974 1.0000 0.0277 -17.000 -0.8527 0.06348 0.05978 -0.0988 1.0000 0.0278 -16.750 -0.8547 0.06053 0.05680 -0.0999 1.0000 0.0279 -16.500 -0.8576 0.05757 0.05380 -0.1010 1.0000 0.0280 -16.250 -0.8623 0.05467 0.05084 -0.1019 1.0000 0.0280 -16.000 -0.8667 0.05197 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3.250 0.8003 0.00872 0.00306 -0.0963 0.4443 0.5704 3.500 0.8219 0.00871 0.00317 -0.0950 0.4396 0.6090 3.750 0.8422 0.00876 0.00329 -0.0935 0.4346 0.6434 4.000 0.8611 0.00886 0.00343 -0.0917 0.4295 0.6710 4.250 0.8805 0.00897 0.00358 -0.0900 0.4251 0.6953 4.500 0.9024 0.00900 0.00371 -0.0888 0.4220 0.7213 4.750 0.9216 0.00901 0.00387 -0.0871 0.4184 0.7650 5.000 0.9330 0.00890 0.00411 -0.0836 0.4150 0.8931 5.250 0.9753 0.00907 0.00435 -0.0867 0.4103 0.9642 5.500 1.0196 0.00928 0.00455 -0.0904 0.4062 1.0000 5.750 1.0412 0.00939 0.00468 -0.0892 0.4034 1.0000 6.000 1.0618 0.00954 0.00483 -0.0879 0.3997 1.0000 6.250 1.0807 0.00975 0.00501 -0.0863 0.3953 1.0000 6.500 1.0969 0.01004 0.00525 -0.0843 0.3892 1.0000 6.750 1.1199 0.01015 0.00538 -0.0835 0.3849 1.0000 7.000 1.1397 0.01036 0.00557 -0.0821 0.3794 1.0000 7.250 1.1568 0.01065 0.00583 -0.0804 0.3736 1.0000 7.500 1.1771 0.01087 0.00605 -0.0792 0.3694 1.0000 7.750 1.1982 0.01107 0.00626 -0.0781 0.3647 1.0000 8.000 1.2171 0.01135 0.00652 -0.0768 0.3595 1.0000 8.250 1.2332 0.01173 0.00687 -0.0750 0.3538 1.0000 8.500 1.2550 0.01194 0.00710 -0.0741 0.3489 1.0000 8.750 1.2736 0.01226 0.00742 -0.0728 0.3426 1.0000 9.000 1.2895 0.01269 0.00781 -0.0712 0.3357 1.0000 9.250 1.3087 0.01302 0.00815 -0.0700 0.3277 1.0000 9.500 1.3230 0.01355 0.00864 -0.0683 0.3194 1.0000 9.750 1.3411 0.01396 0.00904 -0.0671 0.3108 1.0000 10.000 1.3548 0.01456 0.00960 -0.0653 0.3013 1.0000 10.250 1.3695 0.01515 0.01016 -0.0638 0.2910 1.0000 10.500 1.3830 0.01582 0.01079 -0.0621 0.2810 1.0000 10.750 1.3942 0.01663 0.01155 -0.0603 0.2702 1.0000 11.000 1.4073 0.01737 0.01226 -0.0587 0.2602 1.0000 11.250 1.4184 0.01824 0.01310 -0.0570 0.2498 1.0000 11.750 1.4400 0.02012 0.01491 -0.0538 0.2304 1.0000 12.000 1.4492 0.02120 0.01595 -0.0522 0.2212 1.0000 12.250 1.4588 0.02230 0.01702 -0.0507 0.2113 1.0000 12.500 1.4691 0.02340 0.01811 -0.0493 0.2026 1.0000 12.750 1.4762 0.02472 0.01938 -0.0477 0.1921 1.0000 13.000 1.4813 0.02624 0.02085 -0.0461 0.1794 1.0000 13.250 1.4844 0.02797 0.02251 -0.0445 0.1644 1.0000 13.500 1.4832 0.03007 0.02453 -0.0427 0.1460 1.0000 13.750 1.4801 0.03240 0.02677 -0.0410 0.1304 1.0000 14.000 1.4770 0.03483 0.02914 -0.0395 0.1178 1.0000 14.250 1.4775 0.03705 0.03134 -0.0382 0.1094 1.0000 14.500 1.4783 0.03930 0.03359 -0.0372 0.1026 1.0000 14.750 1.4811 0.04143 0.03572 -0.0363 0.0976 1.0000 15.000 1.4836 0.04362 0.03792 -0.0354 0.0930 1.0000 15.250 1.4866 0.04580 0.04014 -0.0347 0.0895 1.0000 15.500 1.4872 0.04822 0.04256 -0.0340 0.0861 1.0000 15.750 1.4913 0.05035 0.04474 -0.0334 0.0835 1.0000 16.000 1.4943 0.05263 0.04706 -0.0329 0.0814 1.0000 16.250 1.4954 0.05509 0.04954 -0.0324 0.0790 1.0000 16.500 1.4940 0.05787 0.05235 -0.0319 0.0770 1.0000 16.750 1.4975 0.06014 0.05468 -0.0315 0.0756 1.0000 17.000 1.4999 0.06259 0.05719 -0.0312 0.0744 1.0000 17.250 1.5004 0.06525 0.05990 -0.0310 0.0729 1.0000 17.500 1.5004 0.06797 0.06266 -0.0307 0.0718 1.0000 17.750 1.4980 0.07099 0.06573 -0.0306 0.0706 1.0000 18.000 1.4934 0.07431 0.06910 -0.0305 0.0690 1.0000 18.250 1.4951 0.07694 0.07179 -0.0305 0.0679 1.0000 18.500 1.4954 0.07977 0.07468 -0.0305 0.0670 1.0000 18.750 1.4957 0.08257 0.07754 -0.0306 0.0661 1.0000 19.000 1.4935 0.08572 0.08076 -0.0308 0.0654 1.0000 19.250 1.4916 0.08886 0.08394 -0.0311 0.0643 1.0000