XFOIL Version 6.94 Calculated polar for: SD6080 (9.2%) 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 0.4045 0.00775 0.00273 -0.0815 0.7335 1.0000 0.500 0.4588 0.00790 0.00268 -0.0811 0.7176 1.0000 1.000 0.5133 0.00806 0.00267 -0.0806 0.7011 1.0000 1.500 0.5678 0.00823 0.00270 -0.0801 0.6840 1.0000 2.000 0.6224 0.00841 0.00277 -0.0797 0.6665 1.0000 2.500 0.6768 0.00862 0.00287 -0.0793 0.6483 1.0000 3.000 0.7311 0.00881 0.00304 -0.0788 0.6279 1.0000 3.500 0.7851 0.00901 0.00322 -0.0784 0.6062 1.0000 4.000 0.8387 0.00926 0.00344 -0.0778 0.5832 1.0000 4.500 0.8919 0.00951 0.00371 -0.0772 0.5567 1.0000 5.000 0.9442 0.00983 0.00402 -0.0765 0.5267 1.0000 5.500 0.9955 0.01021 0.00440 -0.0756 0.4900 1.0000 6.000 1.0449 0.01076 0.00489 -0.0745 0.4440 1.0000 6.500 1.0895 0.01167 0.00553 -0.0728 0.3691 1.0000 7.000 1.1317 0.01286 0.00646 -0.0710 0.2948 1.0000 7.500 1.1699 0.01440 0.00763 -0.0688 0.2169 1.0000 8.000 1.2079 0.01591 0.00889 -0.0666 0.1576 1.0000 8.500 1.2428 0.01757 0.01036 -0.0640 0.1034 1.0000 9.000 1.2590 0.02061 0.01285 -0.0590 0.0326 1.0000 9.500 1.2741 0.02303 0.01540 -0.0534 0.0238 1.0000 10.000 1.2912 0.02522 0.01780 -0.0487 0.0209 1.0000 10.500 1.3012 0.02816 0.02096 -0.0442 0.0194 1.0000 11.000 1.3031 0.03220 0.02519 -0.0401 0.0183 1.0000 11.500 1.3063 0.03679 0.03000 -0.0367 0.0175 1.0000 12.000 1.3184 0.04100 0.03447 -0.0342 0.0172 1.0000 12.500 1.3307 0.04565 0.03944 -0.0319 0.0168 1.0000 13.000 1.3396 0.05082 0.04498 -0.0303 0.0163 1.0000 13.500 1.3412 0.05683 0.05137 -0.0294 0.0157 1.0000 14.000 1.3350 0.06417 0.05911 -0.0294 0.0154 1.0000 14.500 1.3178 0.07340 0.06880 -0.0308 0.0154 1.0000 15.000 1.2905 0.08485 0.08071 -0.0345 0.0155 1.0000 15.500 1.2567 0.09862 0.09492 -0.0409 0.0157 1.0000 16.000 1.2181 0.11493 0.11164 -0.0501 0.0159 1.0000 16.500 1.1750 0.13454 0.13161 -0.0625 0.0163 1.0000 17.000 1.1251 0.15898 0.15633 -0.0784 0.0168 1.0000 17.500 1.0813 0.18551 0.18296 -0.0940 0.0180 1.0000 19.500 0.8252 0.23451 0.23236 -0.1123 0.0316 1.0000 20.000 0.8298 0.24381 0.24168 -0.1170 0.0279 1.0000 20.500 0.8399 0.25149 0.24941 -0.1200 0.0258 1.0000 21.000 0.8553 0.26075 0.25869 -0.1212 0.0240 1.0000 21.500 0.8540 0.27039 0.26833 -0.1273 0.0232 1.0000 22.000 0.8604 0.27983 0.27780 -0.1314 0.0199 1.0000 22.500 0.8715 0.28740 0.28540 -0.1339 0.0183 1.0000 23.000 0.8838 0.29771 0.29574 -0.1358 0.0177 1.0000 23.500 0.8824 0.30820 0.30622 -0.1420 0.0161 1.0000 24.000 0.8903 0.31737 0.31543 -0.1453 0.0139 1.0000 24.500 0.9008 0.32533 0.32343 -0.1474 0.0130 1.0000 25.000 0.9038 0.33742 0.33550 -0.1520 0.0123 1.0000 25.500 0.9102 0.34791 0.34602 -0.1557 0.0113 1.0000 26.000 0.9167 0.35762 0.35576 -0.1589 0.0101 1.0000 26.500 0.9232 0.36701 0.36517 -0.1622 0.0095 1.0000 27.000 0.9324 0.37634 0.37456 -0.1641 0.0089 1.0000 27.500 0.9370 0.38722 0.38544 -0.1677 0.0088 1.0000 28.000 0.9401 0.39880 0.39703 -0.1721 0.0077 1.0000 28.500 0.9454 0.40908 0.40733 -0.1753 0.0069 1.0000 29.000 0.9504 0.41916 0.41744 -0.1785 0.0065 1.0000 29.500 0.9553 0.42845 0.42677 -0.1811 0.0059 1.0000 30.000 0.9597 0.43988 0.43821 -0.1840 0.0057 1.0000 30.500 0.9628 0.45100 0.44934 -0.1876 0.0057 1.0000 31.000 0.9669 0.46242 0.46080 -0.1909 0.0053 1.0000 31.500 0.9701 0.47246 0.47087 -0.1940 0.0052 1.0000 32.000 0.9734 0.48365 0.48208 -0.1969 0.0044 1.0000