XFOIL Version 6.96 Calculated polar for: SIKORSKY DBLN-526 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -0.8652 0.07047 0.06473 -0.1733 0.9595 0.0310 -19.500 -0.8680 0.06749 0.06163 -0.1736 0.9592 0.0309 -19.250 -0.8708 0.06461 0.05869 -0.1738 0.9590 0.0312 -19.000 -0.8935 0.06300 0.05704 -0.1682 0.9562 0.0316 -18.750 -0.9013 0.06177 0.05579 -0.1647 0.9542 0.0319 -18.500 -0.9084 0.05947 0.05339 -0.1627 0.9533 0.0317 -18.250 -0.9097 0.05749 0.05133 -0.1613 0.9525 0.0321 -18.000 -0.9041 0.05592 0.04970 -0.1607 0.9518 0.0325 -17.750 -0.8959 0.05435 0.04806 -0.1604 0.9512 0.0327 -17.500 -0.8876 0.05251 0.04616 -0.1603 0.9506 0.0333 -17.250 -0.8750 0.05117 0.04474 -0.1604 0.9502 0.0339 -17.000 -0.8673 0.04939 0.04286 -0.1600 0.9498 0.0338 -16.750 -0.8555 0.04792 0.04132 -0.1598 0.9494 0.0342 -16.500 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0.9718 0.02842 0.02234 -0.0543 0.5060 0.9606 8.000 0.9883 0.02910 0.02298 -0.0530 0.4987 0.9613 8.250 1.0062 0.02975 0.02366 -0.0519 0.4914 0.9625 8.500 1.0265 0.03032 0.02425 -0.0514 0.4851 0.9642 8.750 1.0383 0.03129 0.02518 -0.0493 0.4715 0.9656 9.000 1.0568 0.03194 0.02586 -0.0486 0.4611 0.9664 9.250 1.0709 0.03299 0.02688 -0.0470 0.4505 0.9692 9.500 1.0613 0.03522 0.02888 -0.0413 0.3956 0.9685 9.750 1.0795 0.03598 0.02966 -0.0406 0.3891 0.9688 10.000 1.0492 0.03958 0.03283 -0.0316 0.3197 0.9704 10.250 1.0496 0.04142 0.03452 -0.0282 0.2891 0.9702 10.500 1.0562 0.04291 0.03592 -0.0257 0.2686 0.9722 10.750 1.0657 0.04425 0.03719 -0.0239 0.2483 0.9719 11.250 1.0779 0.04763 0.04039 -0.0194 0.2129 0.9763 11.500 1.0921 0.04867 0.04144 -0.0186 0.2065 0.9758 11.750 1.1101 0.04977 0.04258 -0.0183 0.2046 0.9778 12.000 1.1182 0.05124 0.04402 -0.0167 0.1936 0.9773 12.250 1.1321 0.05237 0.04516 -0.0158 0.1886 0.9783 12.500 1.1430 0.05366 0.04645 -0.0146 0.1775 0.9789 12.750 1.1533 0.05503 0.04782 -0.0133 0.1728 0.9802 13.000 1.1669 0.05623 0.04906 -0.0126 0.1656 0.9805 13.250 1.1764 0.05778 0.05055 -0.0114 0.1540 0.9802 13.500 1.1836 0.05949 0.05221 -0.0099 0.1384 0.9812 13.750 1.1906 0.06124 0.05391 -0.0086 0.1257 0.9813 14.000 1.1872 0.06379 0.05629 -0.0060 0.0989 0.9816