XFOIL Version 6.96 Calculated polar for: GOE 493 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.750 -0.5729 0.11031 0.10615 -0.0628 1.0000 0.0187 -15.500 -0.6252 0.09596 0.09158 -0.0701 1.0000 0.0185 -15.250 -0.6546 0.08709 0.08256 -0.0745 1.0000 0.0183 -15.000 -0.6757 0.08020 0.07554 -0.0779 1.0000 0.0183 -14.750 -0.6947 0.07417 0.06940 -0.0807 1.0000 0.0183 -14.500 -0.7119 0.06875 0.06387 -0.0831 1.0000 0.0185 -14.250 -0.7283 0.06384 0.05886 -0.0850 1.0000 0.0186 -14.000 -0.7437 0.05942 0.05435 -0.0864 1.0000 0.0186 -13.750 -0.7590 0.05541 0.05024 -0.0873 1.0000 0.0188 -13.500 -0.7743 0.05187 0.04662 -0.0875 1.0000 0.0189 -13.250 -0.7912 0.04872 0.04338 -0.0870 1.0000 0.0191 -13.000 -0.8096 0.04594 0.04053 -0.0856 1.0000 0.0192 -12.750 -0.8038 0.04226 0.03666 -0.0897 0.9963 0.0197 -12.500 -0.7942 0.03906 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0.01133 0.00432 -0.0873 0.6593 0.7620 2.000 0.5791 0.01135 0.00441 -0.0864 0.6513 0.7862 2.250 0.6054 0.01137 0.00448 -0.0860 0.6446 0.8124 2.500 0.6314 0.01140 0.00461 -0.0855 0.6368 0.8406 2.750 0.6638 0.01145 0.00470 -0.0863 0.6297 0.8720 3.000 0.7013 0.01154 0.00488 -0.0884 0.6209 0.9067 3.250 0.7477 0.01167 0.00502 -0.0924 0.6132 0.9407 3.500 0.7909 0.01180 0.00520 -0.0959 0.6047 0.9763 3.750 0.8292 0.01199 0.00535 -0.0983 0.5971 1.0000 4.000 0.8481 0.01213 0.00551 -0.0966 0.5888 1.0000 4.250 0.8693 0.01229 0.00563 -0.0954 0.5812 1.0000 4.500 0.8887 0.01245 0.00581 -0.0938 0.5723 1.0000 4.750 0.9097 0.01263 0.00597 -0.0925 0.5640 1.0000 5.000 0.9288 0.01281 0.00615 -0.0908 0.5536 1.0000 5.250 0.9464 0.01300 0.00633 -0.0888 0.5403 1.0000 5.500 0.9629 0.01321 0.00651 -0.0866 0.5249 1.0000 5.750 0.9780 0.01344 0.00669 -0.0842 0.5077 1.0000 6.000 0.9925 0.01370 0.00690 -0.0816 0.4902 1.0000 6.250 1.0059 0.01397 0.00712 -0.0788 0.4726 1.0000 6.500 1.0171 0.01427 0.00738 -0.0757 0.4544 1.0000 6.750 1.0279 0.01461 0.00767 -0.0725 0.4337 1.0000 7.000 1.0362 0.01505 0.00800 -0.0690 0.4098 1.0000 7.250 1.0422 0.01560 0.00842 -0.0653 0.3812 1.0000 7.500 1.0494 0.01621 0.00891 -0.0619 0.3571 1.0000 7.750 1.0567 0.01689 0.00948 -0.0586 0.3335 1.0000 8.000 1.0644 0.01761 0.01011 -0.0556 0.3117 1.0000 8.250 1.0741 0.01831 0.01076 -0.0530 0.2904 1.0000 8.500 1.0818 0.01913 0.01149 -0.0502 0.2653 1.0000 8.750 1.0862 0.02016 0.01237 -0.0471 0.2264 1.0000 9.000 1.0797 0.02183 0.01368 -0.0429 0.1710 1.0000 9.250 1.0792 0.02336 0.01502 -0.0397 0.1388 1.0000 9.500 1.0819 0.02478 0.01632 -0.0370 0.1096 1.0000 9.750 1.0831 0.02636 0.01774 -0.0344 0.0847 1.0000 10.000 1.0868 0.02783 0.01914 -0.0321 0.0712 1.0000 10.250 1.0934 0.02917 0.02049 -0.0302 0.0622 1.0000 10.500 1.1003 0.03053 0.02187 -0.0285 0.0569 1.0000 10.750 1.1072 0.03193 0.02332 -0.0269 0.0529 1.0000 11.000 1.1124 0.03350 0.02491 -0.0252 0.0500 1.0000 11.250 1.1198 0.03495 0.02644 -0.0238 0.0477 1.0000 11.500 1.1263 0.03652 0.02808 -0.0225 0.0456 1.0000 11.750 1.1317 0.03822 0.02984 -0.0212 0.0440 1.0000 12.000 1.1347 0.04018 0.03185 -0.0199 0.0425 1.0000 12.250 1.1386 0.04214 0.03386 -0.0188 0.0413 1.0000 12.500 1.1444 0.04397 0.03581 -0.0179 0.0401 1.0000 12.750 1.1501 0.04587 0.03779 -0.0170 0.0387 1.0000 13.000 1.1543 0.04793 0.03994 -0.0162 0.0377 1.0000 13.250 1.1583 0.05008 0.04215 -0.0155 0.0366 1.0000 13.500 1.1606 0.05245 0.04456 -0.0149 0.0356 1.0000 13.750 1.1610 0.05503 0.04716 -0.0142 0.0345 1.0000 14.000 1.1673 0.05708 0.04933 -0.0138 0.0337 1.0000 14.250 1.1727 0.05924 0.05161 -0.0134 0.0328 1.0000 14.500 1.1777 0.06149 0.05395 -0.0130 0.0319 1.0000 14.750 1.1824 0.06381 0.05635 -0.0128 0.0308 1.0000 15.000 1.1863 0.06622 0.05882 -0.0127 0.0299 1.0000 15.250 1.1896 0.06872 0.06137 -0.0125 0.0291 1.0000 15.500 1.1930 0.07115 0.06379 -0.0122 0.0283 1.0000 15.750 1.1983 0.07355 0.06634 -0.0122 0.0276 1.0000 16.000 1.2027 0.07609 0.06903 -0.0123 0.0268 1.0000 16.250 1.2065 0.07870 0.07177 -0.0124 0.0260 1.0000 16.500 1.2096 0.08145 0.07462 -0.0127 0.0251 1.0000 16.750 1.2119 0.08434 0.07758 -0.0132 0.0243 1.0000 17.000 1.2149 0.08711 0.08041 -0.0136 0.0238 1.0000 17.250 1.2177 0.08987 0.08320 -0.0139 0.0232 1.0000 17.500 1.2192 0.09298 0.08645 -0.0145 0.0226 1.0000 17.750 1.2190 0.09642 0.09008 -0.0153 0.0220 1.0000 18.000 1.2183 0.09998 0.09381 -0.0163 0.0214 1.0000 18.250 1.2166 0.10376 0.09774 -0.0176 0.0207 1.0000 18.500 1.2152 0.10751 0.10163 -0.0189 0.0202 1.0000