XFOIL Version 6.96 Calculated polar for: A18 (smoothed) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -4.500 -0.3004 0.05511 0.05039 -0.0489 1.0000 0.1522 -4.000 -0.2516 0.04795 0.04301 -0.0551 1.0000 0.1702 -3.900 -0.1595 0.02885 0.02139 -0.0793 1.0000 0.0751 -3.800 -0.1453 0.02725 0.01954 -0.0804 1.0000 0.0754 -3.700 -0.1312 0.02570 0.01778 -0.0815 1.0000 0.0766 -3.600 -0.1188 0.02476 0.01674 -0.0820 1.0000 0.0786 -3.500 -0.1071 0.02417 0.01608 -0.0823 1.0000 0.0812 -3.400 -0.0952 0.02365 0.01547 -0.0826 1.0000 0.0845 -3.300 -0.0829 0.02313 0.01481 -0.0829 1.0000 0.0886 -3.200 -0.0705 0.02266 0.01416 -0.0831 1.0000 0.0927 -3.100 -0.0574 0.02197 0.01330 -0.0836 1.0000 0.0981 -3.000 -0.0483 0.02189 0.01338 -0.0837 1.0000 0.1055 -2.900 -0.0388 0.02192 0.01340 -0.0835 1.0000 0.1126 -2.800 -0.0277 0.02175 0.01308 -0.0835 1.0000 0.1184 -2.700 -0.0130 0.02076 0.01201 -0.0844 1.0000 0.1252 -2.600 -0.0023 0.02052 0.01183 -0.0844 1.0000 0.1322 -2.500 0.0087 0.02034 0.01158 -0.0845 1.0000 0.1402 -2.400 0.0207 0.02002 0.01116 -0.0847 1.0000 0.1489 -2.300 0.0307 0.01986 0.01113 -0.0848 1.0000 0.1599 -2.200 0.0402 0.01993 0.01116 -0.0847 1.0000 0.1711 -2.100 0.0522 0.01955 0.01080 -0.0851 1.0000 0.1824 -2.000 0.0625 0.01945 0.01075 -0.0851 1.0000 0.1924 -1.900 0.0729 0.01942 0.01064 -0.0851 1.0000 0.2028 -1.800 0.0844 0.01914 0.01044 -0.0854 1.0000 0.2152 -1.700 0.0939 0.01917 0.01051 -0.0854 1.0000 0.2281 -1.600 0.1042 0.01911 0.01044 -0.0855 1.0000 0.2413 -1.500 0.1144 0.01902 0.01044 -0.0856 1.0000 0.2544 -1.400 0.1243 0.01904 0.01044 -0.0856 1.0000 0.2675 -1.300 0.1354 0.01890 0.01028 -0.0858 1.0000 0.2811 -1.200 0.1451 0.01895 0.01037 -0.0859 1.0000 0.2971 -1.100 0.1555 0.01891 0.01040 -0.0861 1.0000 0.3148 -1.000 0.1654 0.01895 0.01050 -0.0862 1.0000 0.3337 -1.000 0.1727 0.01875 0.01027 -0.0872 1.0000 0.3518 -0.500 0.2384 0.01823 0.01063 -0.0904 0.9971 0.5538 0.000 0.3203 0.01759 0.01049 -0.0959 0.9783 1.0000 0.500 0.4100 0.01806 0.01065 -0.1035 0.9595 1.0000 1.000 0.4923 0.01833 0.01079 -0.1093 0.9382 1.0000 1.500 0.5761 0.01835 0.01079 -0.1149 0.9180 1.0000 2.000 0.6565 0.01820 0.01072 -0.1194 0.8972 1.0000 2.500 0.7330 0.01785 0.01049 -0.1226 0.8758 1.0000 3.000 0.8028 0.01723 0.01006 -0.1235 0.8486 1.0000 3.500 0.8656 0.01622 0.00916 -0.1216 0.8097 1.0000 4.000 0.9227 0.01592 0.00903 -0.1196 0.7717 1.0000 4.500 0.9743 0.01589 0.00912 -0.1167 0.7241 1.0000 5.000 1.0220 0.01589 0.00916 -0.1128 0.6575 1.0000 5.500 1.0627 0.01628 0.00939 -0.1078 0.5530 1.0000 6.000 1.0856 0.01852 0.01036 -0.1008 0.2953 1.0000 6.500 1.0985 0.02374 0.01400 -0.0939 0.1157 1.0000 7.000 1.1314 0.02755 0.01750 -0.0898 0.0809 1.0000 7.500 1.1766 0.03140 0.02148 -0.0875 0.0645 1.0000 8.000 1.2296 0.03738 0.02761 -0.0866 0.0574 1.0000 8.500 1.2684 0.04239 0.03356 -0.0830 0.0523 1.0000 9.000 1.2944 0.05030 0.04253 -0.0781 0.0524 1.0000 9.500 1.3010 0.05990 0.05315 -0.0720 0.0550 1.0000 10.000 1.2960 0.07000 0.06389 -0.0666 0.0569 1.0000