XFOIL Version 6.96 Calculated polar for: GOE 681 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 -0.6919 0.12556 0.12291 -0.0529 1.0000 0.0230 -18.750 -0.7203 0.11666 0.11389 -0.0578 1.0000 0.0231 -18.500 -0.7397 0.10966 0.10678 -0.0616 1.0000 0.0231 -18.250 -0.7555 0.10343 0.10048 -0.0650 1.0000 0.0232 -18.000 -0.7711 0.09743 0.09439 -0.0682 1.0000 0.0232 -17.750 -0.7826 0.09227 0.08916 -0.0709 1.0000 0.0233 -17.500 -0.7972 0.08671 0.08352 -0.0739 1.0000 0.0233 -17.250 -0.8099 0.08159 0.07834 -0.0766 1.0000 0.0234 -17.000 -0.8244 0.07645 0.07313 -0.0793 1.0000 0.0235 -16.750 -0.8439 0.07099 0.06759 -0.0821 1.0000 0.0234 -16.500 -0.8645 0.06544 0.06195 -0.0850 1.0000 0.0235 -16.250 -0.8852 0.05995 0.05637 -0.0877 1.0000 0.0235 -16.000 -0.9073 0.05419 0.05053 -0.0907 1.0000 0.0235 -15.750 -0.9268 0.04867 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-0.0811 0.4708 0.1696 -1.000 0.3237 0.00906 0.00218 -0.0803 0.4571 0.1788 -0.750 0.3477 0.00914 0.00220 -0.0793 0.4400 0.1851 -0.500 0.3712 0.00924 0.00224 -0.0783 0.4213 0.1921 -0.250 0.3946 0.00937 0.00229 -0.0773 0.4016 0.1973 0.000 0.4173 0.00948 0.00235 -0.0761 0.3820 0.2055 0.250 0.4403 0.00960 0.00241 -0.0751 0.3655 0.2114 0.500 0.4635 0.00974 0.00247 -0.0740 0.3509 0.2151 0.750 0.4872 0.00984 0.00252 -0.0730 0.3389 0.2195 1.000 0.5104 0.00992 0.00259 -0.0720 0.3293 0.2275 1.250 0.5338 0.01000 0.00265 -0.0710 0.3205 0.2353 1.500 0.5570 0.01008 0.00272 -0.0699 0.3130 0.2443 1.750 0.5804 0.01015 0.00279 -0.0689 0.3057 0.2522 2.000 0.6026 0.01025 0.00287 -0.0677 0.2982 0.2627 2.250 0.6260 0.01029 0.00294 -0.0667 0.2938 0.2756 2.500 0.6485 0.01034 0.00302 -0.0656 0.2884 0.2938 2.750 0.6696 0.01038 0.00310 -0.0642 0.2834 0.3202 3.000 0.6892 0.01038 0.00319 -0.0624 0.2791 0.3567 3.250 0.7087 0.01034 0.00327 -0.0607 0.2758 0.4046 3.500 0.7276 0.01030 0.00337 -0.0589 0.2720 0.4566 3.750 0.7462 0.01031 0.00349 -0.0570 0.2680 0.5060 4.000 0.7634 0.01032 0.00364 -0.0548 0.2638 0.5646 4.250 0.7762 0.01013 0.00381 -0.0518 0.2612 0.6910 4.500 0.7851 0.00990 0.00399 -0.0477 0.2586 0.8256 4.750 0.8762 0.01007 0.00441 -0.0613 0.2516 0.9542 5.000 0.9446 0.01044 0.00472 -0.0701 0.2456 0.9778 5.250 0.9823 0.01065 0.00491 -0.0723 0.2431 0.9911 5.500 1.0184 0.01089 0.00513 -0.0742 0.2402 0.9995 5.750 1.0382 0.01105 0.00527 -0.0726 0.2375 1.0000 6.000 1.0516 0.01121 0.00542 -0.0698 0.2350 1.0000 6.250 1.0664 0.01139 0.00559 -0.0673 0.2324 1.0000 6.500 1.0819 0.01160 0.00578 -0.0649 0.2294 1.0000 6.750 1.1000 0.01177 0.00596 -0.0631 0.2276 1.0000 7.000 1.1181 0.01197 0.00615 -0.0613 0.2254 1.0000 7.250 1.1357 0.01220 0.00637 -0.0595 0.2220 1.0000 7.500 1.1531 0.01247 0.00662 -0.0577 0.2189 1.0000 7.750 1.1703 0.01276 0.00690 -0.0559 0.2161 1.0000 8.000 1.1884 0.01304 0.00718 -0.0543 0.2136 1.0000 8.250 1.2077 0.01329 0.00744 -0.0530 0.2121 1.0000 8.500 1.2267 0.01357 0.00773 -0.0516 0.2103 1.0000 8.750 1.2455 0.01388 0.00805 -0.0503 0.2088 1.0000 9.000 1.2637 0.01421 0.00839 -0.0489 0.2066 1.0000 9.250 1.2813 0.01460 0.00877 -0.0476 0.2040 1.0000 9.500 1.2981 0.01503 0.00920 -0.0461 0.2011 1.0000 9.750 1.3161 0.01544 0.00961 -0.0449 0.1984 1.0000 10.000 1.3346 0.01583 0.01001 -0.0437 0.1957 1.0000 10.250 1.3523 0.01627 0.01047 -0.0426 0.1927 1.0000 10.500 1.3695 0.01676 0.01096 -0.0414 0.1907 1.0000 10.750 1.3861 0.01730 0.01150 -0.0402 0.1885 1.0000 11.000 1.4020 0.01789 0.01210 -0.0390 0.1859 1.0000 11.250 1.4197 0.01840 0.01264 -0.0380 0.1843 1.0000 11.500 1.4371 0.01895 0.01321 -0.0370 0.1818 1.0000 11.750 1.4534 0.01956 0.01384 -0.0360 0.1792 1.0000 12.000 1.4670 0.02036 0.01462 -0.0348 0.1743 1.0000 12.250 1.4820 0.02109 0.01537 -0.0337 0.1713 1.0000 12.500 1.4972 0.02182 0.01612 -0.0327 0.1673 1.0000 12.750 1.5095 0.02275 0.01704 -0.0316 0.1620 1.0000 13.000 1.5216 0.02373 0.01801 -0.0305 0.1563 1.0000 13.250 1.5313 0.02487 0.01912 -0.0292 0.1491 1.0000 13.500 1.5385 0.02622 0.02044 -0.0279 0.1397 1.0000 13.750 1.5418 0.02789 0.02206 -0.0263 0.1284 1.0000 14.000 1.5406 0.02995 0.02405 -0.0247 0.1154 1.0000 14.250 1.5355 0.03239 0.02643 -0.0229 0.1006 1.0000 14.500 1.5262 0.03530 0.02927 -0.0212 0.0863 1.0000 14.750 1.5207 0.03801 0.03195 -0.0200 0.0764 1.0000 15.000 1.5182 0.04056 0.03451 -0.0190 0.0692 1.0000 15.250 1.5124 0.04352 0.03746 -0.0181 0.0602 1.0000 15.500 1.4907 0.04817 0.04204 -0.0171 0.0419 1.0000 16.000 1.4736 0.05533 0.04927 -0.0165 0.0317 1.0000 16.250 1.4709 0.05841 0.05241 -0.0164 0.0304 1.0000 16.500 1.4688 0.06149 0.05556 -0.0165 0.0294 1.0000 16.750 1.4661 0.06469 0.05882 -0.0166 0.0286 1.0000 17.000 1.4615 0.06818 0.06239 -0.0169 0.0280 1.0000 17.250 1.4547 0.07200 0.06629 -0.0173 0.0273 1.0000 17.500 1.4482 0.07586 0.07023 -0.0178 0.0270 1.0000 17.750 1.4402 0.07999 0.07444 -0.0185 0.0266 1.0000 18.000 1.4327 0.08410 0.07864 -0.0192 0.0263 1.0000 18.250 1.4240 0.08840 0.08304 -0.0201 0.0261 1.0000 18.500 1.4139 0.09299 0.08772 -0.0211 0.0258 1.0000 18.750 1.4031 0.09775 0.09258 -0.0223 0.0256 1.0000 19.000 1.3908 0.10273 0.09766 -0.0236 0.0253 1.0000 19.250 1.3782 0.10782 0.10284 -0.0250 0.0252 1.0000