XFOIL Version 6.94 Calculated polar for: S4022 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.6897 0.00771 0.00269 -0.1673 0.7966 0.6909 0.500 0.7445 0.00781 0.00274 -0.1669 0.7797 0.7090 1.000 0.7977 0.00789 0.00282 -0.1662 0.7614 0.7260 1.500 0.8500 0.00799 0.00294 -0.1654 0.7418 0.7434 2.000 0.9018 0.00810 0.00306 -0.1644 0.7205 0.7621 2.500 0.9531 0.00826 0.00322 -0.1634 0.6982 0.7828 3.000 1.0025 0.00841 0.00341 -0.1619 0.6724 0.8068 3.500 1.0494 0.00860 0.00366 -0.1599 0.6438 0.8351 4.000 1.0930 0.00881 0.00391 -0.1572 0.6132 0.8741 4.500 1.1289 0.00890 0.00406 -0.1527 0.5784 1.0000 5.000 1.1762 0.00944 0.00448 -0.1513 0.5380 1.0000 5.500 1.2201 0.01007 0.00496 -0.1491 0.4919 1.0000 6.000 1.2597 0.01086 0.00556 -0.1461 0.4396 1.0000 6.500 1.2929 0.01191 0.00632 -0.1420 0.3700 1.0000 7.000 1.3196 0.01326 0.00733 -0.1369 0.2910 1.0000 7.500 1.3437 0.01491 0.00856 -0.1315 0.2115 1.0000 8.000 1.3649 0.01682 0.01004 -0.1261 0.1371 1.0000 8.500 1.3900 0.01851 0.01152 -0.1214 0.0936 1.0000 9.000 1.4150 0.02022 0.01315 -0.1169 0.0647 1.0000 9.500 1.4359 0.02225 0.01507 -0.1120 0.0373 1.0000 10.000 1.4462 0.02520 0.01795 -0.1059 0.0151 1.0000 10.500 1.4598 0.02805 0.02094 -0.1009 0.0116 1.0000 11.000 1.4679 0.03153 0.02470 -0.0958 0.0105 1.0000 11.500 1.4771 0.03517 0.02861 -0.0915 0.0097 1.0000 12.000 1.4818 0.03951 0.03322 -0.0877 0.0091 1.0000 12.500 1.4845 0.04442 0.03838 -0.0845 0.0084 1.0000 13.000 1.4855 0.04987 0.04405 -0.0821 0.0078 1.0000 13.500 1.4777 0.05692 0.05136 -0.0803 0.0071 1.0000 14.000 1.4603 0.06612 0.06098 -0.0789 0.0067 1.0000 14.500 1.4533 0.07435 0.06957 -0.0790 0.0065 1.0000 15.000 1.4448 0.08320 0.07878 -0.0803 0.0064 1.0000 15.500 1.4309 0.09351 0.08946 -0.0830 0.0063 1.0000 16.000 1.4114 0.10541 0.10175 -0.0874 0.0063 1.0000 16.500 1.3895 0.11854 0.11525 -0.0935 0.0062 1.0000 17.000 1.3621 0.13361 0.13070 -0.1017 0.0062 1.0000 17.500 1.3332 0.15020 0.14763 -0.1120 0.0063 1.0000 18.000 1.3029 0.16852 0.16628 -0.1241 0.0063 1.0000 19.000 1.2409 0.21132 0.20955 -0.1524 0.0067 1.0000