XFOIL Version 6.96 Calculated polar for: AS5048 (18%) 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -0.9732 0.11784 0.11493 -0.0329 1.0000 0.0049 -19.500 -0.9962 0.10965 0.10660 -0.0369 1.0000 0.0049 -19.250 -1.0152 0.10247 0.09927 -0.0404 1.0000 0.0049 -19.000 -1.0324 0.09582 0.09249 -0.0434 1.0000 0.0049 -18.750 -1.0463 0.08987 0.08641 -0.0460 1.0000 0.0049 -18.500 -1.0578 0.08447 0.08090 -0.0481 1.0000 0.0049 -18.250 -1.0674 0.07955 0.07586 -0.0500 1.0000 0.0049 -18.000 -1.0755 0.07498 0.07119 -0.0516 1.0000 0.0050 -17.750 -1.0814 0.07086 0.06697 -0.0528 1.0000 0.0050 -17.500 -1.0831 0.06681 0.06280 -0.0547 0.9997 0.0050 -17.250 -1.0790 0.06292 0.05880 -0.0573 0.9989 0.0050 -17.000 -1.0746 0.05934 0.05512 -0.0595 0.9974 0.0051 -16.750 -1.0735 0.05636 0.05206 -0.0600 0.9940 0.0051 -16.250 -1.0086 0.04842 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0.6470 3.000 0.6077 0.00789 0.00223 -0.0589 0.4636 0.6483 3.250 0.6328 0.00815 0.00238 -0.0586 0.4375 0.6495 3.500 0.6575 0.00842 0.00255 -0.0581 0.4092 0.6506 3.750 0.6823 0.00869 0.00271 -0.0577 0.3853 0.6517 4.000 0.7075 0.00893 0.00287 -0.0574 0.3649 0.6527 4.250 0.7320 0.00918 0.00304 -0.0570 0.3429 0.6541 4.500 0.7557 0.00947 0.00324 -0.0564 0.3196 0.6556 4.750 0.7793 0.00976 0.00344 -0.0558 0.2958 0.6568 5.000 0.8022 0.01008 0.00367 -0.0550 0.2730 0.6581 5.250 0.8258 0.01035 0.00388 -0.0545 0.2552 0.6593 5.500 0.8490 0.01064 0.00410 -0.0538 0.2368 0.6606 5.750 0.8721 0.01093 0.00433 -0.0531 0.2212 0.6619 6.000 0.8950 0.01122 0.00456 -0.0524 0.2068 0.6634 6.500 0.9396 0.01182 0.00506 -0.0508 0.1797 0.6662 6.750 0.9621 0.01210 0.00531 -0.0500 0.1698 0.6674 7.000 0.9839 0.01240 0.00557 -0.0491 0.1606 0.6685 7.250 1.0063 0.01266 0.00582 -0.0484 0.1533 0.6695 7.500 1.0272 0.01297 0.00610 -0.0473 0.1454 0.6705 7.750 1.0475 0.01320 0.00635 -0.0461 0.1393 0.6720 8.000 1.0643 0.01352 0.00665 -0.0443 0.1318 0.6734 8.250 1.0844 0.01379 0.00695 -0.0431 0.1262 0.6748 8.500 1.1026 0.01419 0.00732 -0.0417 0.1185 0.6763 8.750 1.1226 0.01452 0.00767 -0.0406 0.1129 0.6778 9.000 1.1398 0.01499 0.00810 -0.0391 0.1044 0.6795 9.250 1.1582 0.01540 0.00852 -0.0378 0.0984 0.6811 9.500 1.1744 0.01592 0.00901 -0.0363 0.0911 0.6826 9.750 1.1908 0.01643 0.00952 -0.0348 0.0847 0.6840 10.000 1.2064 0.01700 0.01008 -0.0333 0.0791 0.6853 10.250 1.2220 0.01759 0.01067 -0.0318 0.0740 0.6865 10.500 1.2365 0.01826 0.01134 -0.0303 0.0690 0.6878 10.750 1.2518 0.01892 0.01203 -0.0291 0.0649 0.6894 11.000 1.2649 0.01974 0.01285 -0.0277 0.0604 0.6911 11.250 1.2800 0.02050 0.01365 -0.0267 0.0569 0.6927 11.500 1.2931 0.02145 0.01461 -0.0256 0.0531 0.6944 11.750 1.3070 0.02239 0.01558 -0.0247 0.0500 0.6961 12.000 1.3206 0.02340 0.01662 -0.0239 0.0470 0.6978 12.250 1.3328 0.02454 0.01778 -0.0230 0.0440 0.6995 12.500 1.3468 0.02557 0.01885 -0.0224 0.0421 0.7013 12.750 1.3593 0.02672 0.02002 -0.0217 0.0399 0.7030 13.250 1.3829 0.02916 0.02254 -0.0203 0.0364 0.7069 13.500 1.3950 0.03035 0.02379 -0.0196 0.0349 0.7091 13.750 1.4057 0.03164 0.02513 -0.0189 0.0335 0.7112 14.000 1.4148 0.03307 0.02660 -0.0181 0.0321 0.7134 14.250 1.4244 0.03447 0.02804 -0.0174 0.0308 0.7156 14.500 1.4340 0.03587 0.02950 -0.0167 0.0297 0.7177 14.750 1.4423 0.03737 0.03105 -0.0160 0.0285 0.7198 15.250 1.4556 0.04074 0.03452 -0.0146 0.0262 0.7247 15.500 1.4638 0.04234 0.03620 -0.0141 0.0255 0.7276 15.750 1.4705 0.04409 0.03802 -0.0135 0.0247 0.7307 16.000 1.4766 0.04594 0.03994 -0.0130 0.0239 0.7338 16.250 1.4803 0.04808 0.04212 -0.0126 0.0227 0.7369 16.500 1.4848 0.05019 0.04430 -0.0122 0.0220 0.7409 16.750 1.4898 0.05232 0.04654 -0.0121 0.0213 0.7460 17.000 1.4940 0.05455 0.04884 -0.0119 0.0203 0.7514 17.250 1.4966 0.05702 0.05139 -0.0118 0.0195 0.7576 17.500 1.4975 0.05974 0.05420 -0.0119 0.0187 0.7661 17.750 1.4991 0.06247 0.05704 -0.0121 0.0180 0.7768 18.000 1.5014 0.06520 0.05989 -0.0124 0.0175 0.7945 18.250 1.5031 0.06813 0.06309 -0.0131 0.0169 0.8511 18.500 1.4847 0.07005 0.06530 -0.0086 0.0167 0.9795 18.750 1.4801 0.07324 0.06857 -0.0085 0.0163 0.9868