XFOIL Version 6.96 Calculated polar for: EPPLER 559 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.250 -0.6447 0.12609 0.12313 -0.0435 1.0000 0.0170 -17.000 -0.6793 0.11501 0.11187 -0.0494 1.0000 0.0170 -16.750 -0.7015 0.10699 0.10370 -0.0536 1.0000 0.0169 -16.500 -0.7195 0.09997 0.09656 -0.0574 1.0000 0.0170 -16.250 -0.7340 0.09386 0.09032 -0.0606 1.0000 0.0170 -16.000 -0.7463 0.08828 0.08462 -0.0635 1.0000 0.0171 -15.750 -0.7574 0.08299 0.07921 -0.0664 1.0000 0.0173 -15.500 -0.7658 0.07839 0.07451 -0.0686 1.0000 0.0173 -15.250 -0.7751 0.07374 0.06975 -0.0711 1.0000 0.0174 -15.000 -0.7813 0.06993 0.06585 -0.0726 1.0000 0.0175 -14.750 -0.7845 0.06721 0.06313 -0.0726 1.0000 0.0180 -14.500 -0.7865 0.06426 0.06017 -0.0735 1.0000 0.0183 -14.250 -0.7904 0.06126 0.05711 -0.0742 1.0000 0.0184 -14.000 -0.7950 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1.000 0.6798 0.01006 0.00311 -0.1314 0.5072 0.4289 1.250 0.7065 0.01017 0.00317 -0.1311 0.4997 0.4379 1.500 0.7338 0.01022 0.00326 -0.1309 0.4924 0.4474 1.750 0.7605 0.01031 0.00333 -0.1306 0.4848 0.4567 2.000 0.7874 0.01039 0.00343 -0.1304 0.4780 0.4671 2.250 0.8143 0.01046 0.00352 -0.1301 0.4711 0.4779 2.500 0.8406 0.01060 0.00363 -0.1298 0.4648 0.4898 2.750 0.8678 0.01064 0.00375 -0.1296 0.4583 0.5026 3.000 0.8941 0.01074 0.00387 -0.1292 0.4517 0.5169 3.250 0.9207 0.01085 0.00401 -0.1289 0.4458 0.5329 3.500 0.9474 0.01091 0.00415 -0.1287 0.4399 0.5511 3.750 0.9733 0.01104 0.00429 -0.1283 0.4341 0.5723 4.000 0.9997 0.01111 0.00446 -0.1280 0.4284 0.5979 4.250 1.0259 0.01118 0.00463 -0.1276 0.4226 0.6284 4.500 1.0512 0.01130 0.00482 -0.1271 0.4172 0.6651 4.750 1.0767 0.01134 0.00503 -0.1266 0.4120 0.7123 5.000 1.1009 0.01135 0.00523 -0.1258 0.4065 0.7721 5.250 1.1197 0.01135 0.00542 -0.1237 0.4015 0.8575 5.500 1.1407 0.01131 0.00552 -0.1221 0.3966 1.0000 5.750 1.1666 0.01147 0.00569 -0.1217 0.3911 1.0000 6.000 1.1916 0.01170 0.00588 -0.1212 0.3859 1.0000 6.250 1.2168 0.01193 0.00610 -0.1208 0.3809 1.0000 6.500 1.2421 0.01209 0.00629 -0.1203 0.3755 1.0000 6.750 1.2662 0.01232 0.00650 -0.1196 0.3702 1.0000 7.000 1.2902 0.01258 0.00674 -0.1190 0.3651 1.0000 7.250 1.3146 0.01275 0.00695 -0.1183 0.3599 1.0000 7.500 1.3376 0.01299 0.00719 -0.1175 0.3545 1.0000 7.750 1.3601 0.01327 0.00745 -0.1165 0.3491 1.0000 8.000 1.3827 0.01344 0.00768 -0.1156 0.3437 1.0000 8.250 1.4032 0.01371 0.00793 -0.1143 0.3379 1.0000 8.500 1.4238 0.01398 0.00822 -0.1130 0.3324 1.0000 8.750 1.4449 0.01420 0.00849 -0.1118 0.3264 1.0000 9.000 1.4633 0.01454 0.00879 -0.1102 0.3203 1.0000 9.250 1.4841 0.01478 0.00910 -0.1090 0.3143 1.0000 9.500 1.5030 0.01509 0.00942 -0.1075 0.3079 1.0000 9.750 1.5206 0.01546 0.00980 -0.1058 0.3015 1.0000 10.000 1.5400 0.01576 0.01015 -0.1045 0.2945 1.0000 10.500 1.5744 0.01654 0.01098 -0.1012 0.2804 1.0000 11.000 1.6054 0.01748 0.01195 -0.0975 0.2641 1.0000 11.250 1.6181 0.01809 0.01255 -0.0954 0.2557 1.0000 11.500 1.6321 0.01867 0.01316 -0.0935 0.2461 1.0000 11.750 1.6441 0.01936 0.01386 -0.0914 0.2366 1.0000 12.000 1.6527 0.02024 0.01472 -0.0890 0.2264 1.0000 12.250 1.6615 0.02115 0.01563 -0.0867 0.2144 1.0000 12.500 1.6678 0.02226 0.01672 -0.0844 0.2015 1.0000 12.750 1.6721 0.02354 0.01798 -0.0819 0.1888 1.0000 13.000 1.6744 0.02503 0.01944 -0.0795 0.1767 1.0000 13.250 1.6741 0.02680 0.02118 -0.0771 0.1641 1.0000 13.500 1.6721 0.02880 0.02316 -0.0749 0.1522 1.0000 13.750 1.6683 0.03110 0.02543 -0.0729 0.1407 1.0000 14.000 1.6665 0.03338 0.02772 -0.0712 0.1306 1.0000 14.250 1.6631 0.03594 0.03029 -0.0698 0.1213 1.0000 14.500 1.6576 0.03883 0.03319 -0.0686 0.1134 1.0000 14.750 1.6530 0.04180 0.03619 -0.0677 0.1054 1.0000 15.000 1.6479 0.04496 0.03939 -0.0670 0.0994 1.0000 15.250 1.6411 0.04845 0.04292 -0.0666 0.0928 1.0000 15.500 1.6343 0.05207 0.04659 -0.0664 0.0874 1.0000 15.750 1.6268 0.05593 0.05050 -0.0664 0.0820 1.0000 16.000 1.6179 0.06009 0.05472 -0.0667 0.0775 1.0000 16.250 1.6113 0.06411 0.05880 -0.0671 0.0730 1.0000 16.500 1.5999 0.06887 0.06361 -0.0678 0.0689 1.0000 16.750 1.5933 0.07313 0.06796 -0.0686 0.0653 1.0000 17.000 1.5841 0.07783 0.07272 -0.0696 0.0617 1.0000 17.250 1.5720 0.08309 0.07803 -0.0709 0.0583 1.0000 17.500 1.5666 0.08746 0.08249 -0.0720 0.0552 1.0000