XFOIL Version 6.94 Calculated polar for: AH 83-159 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3292 0.01766 0.01245 -0.0606 0.7045 0.8877 0.500 0.3777 0.01756 0.01225 -0.0598 0.7000 0.8988 1.000 0.4315 0.01719 0.01179 -0.0595 0.6961 0.9051 1.500 0.4825 0.01755 0.01208 -0.0596 0.6910 0.9107 2.000 0.5244 0.01773 0.01231 -0.0586 0.6846 0.9170 2.500 0.5699 0.01768 0.01229 -0.0577 0.6774 0.9211 3.000 0.6242 0.01735 0.01194 -0.0579 0.6716 0.9260 3.500 0.6842 0.01711 0.01168 -0.0595 0.6673 0.9286 4.000 0.7499 0.01687 0.01141 -0.0618 0.6614 0.9307 4.500 0.7916 0.01709 0.01177 -0.0607 0.6534 0.9349 5.000 0.8415 0.01695 0.01172 -0.0606 0.6446 0.9377 5.500 0.9049 0.01640 0.01127 -0.0624 0.6381 0.9396 6.000 0.9724 0.01592 0.01081 -0.0648 0.6315 0.9413 6.500 1.0171 0.01606 0.01114 -0.0641 0.6204 0.9443 7.000 1.0752 0.01555 0.01075 -0.0650 0.6090 0.9473 7.500 1.1368 0.01473 0.01004 -0.0661 0.5935 0.9495 8.000 1.1821 0.01445 0.00993 -0.0650 0.5742 0.9522 8.500 1.2212 0.01431 0.00987 -0.0628 0.5423 0.9555 9.000 1.2397 0.01514 0.01050 -0.0581 0.4817 0.9603 9.500 1.2056 0.01960 0.01408 -0.0491 0.3551 0.9696 10.500 1.2138 0.02688 0.02105 -0.0435 0.2468 1.0000 11.000 1.2089 0.03162 0.02547 -0.0404 0.1794 1.0000 11.500 1.1912 0.03769 0.03093 -0.0370 0.0962 1.0000 12.500 1.2129 0.04605 0.03925 -0.0347 0.0435 1.0000 13.000 1.2161 0.05107 0.04422 -0.0334 0.0252 1.0000 13.500 1.1890 0.05971 0.05298 -0.0309 0.0092 1.0000 14.000 1.1898 0.06586 0.05942 -0.0303 0.0082 1.0000 14.500 1.1924 0.07182 0.06563 -0.0301 0.0081 1.0000 15.000 1.1959 0.07763 0.07167 -0.0299 0.0080 1.0000 15.500 1.1979 0.08328 0.07760 -0.0288 0.0075 1.0000 16.000 1.2065 0.08854 0.08315 -0.0285 0.0075 1.0000 16.500 1.2087 0.09486 0.08989 -0.0280 0.0077 1.0000 17.000 1.2009 0.10321 0.09868 -0.0292 0.0078 1.0000 17.500 1.1872 0.11279 0.10867 -0.0323 0.0081 1.0000 18.000 1.1630 0.12474 0.12105 -0.0375 0.0082 1.0000 18.500 1.1355 0.13794 0.13465 -0.0447 0.0084 1.0000 19.000 1.0996 0.15400 0.15110 -0.0549 0.0086 1.0000 19.500 1.0641 0.17290 0.17032 -0.0670 0.0088 1.0000 20.000 1.0174 0.19955 0.19723 -0.0821 0.0092 1.0000