XFOIL Version 6.94 Calculated polar for: S7055 (10.5%) Flat-Bottomed 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 0.4355 0.00795 0.00288 -0.0847 0.7388 1.0000 0.500 0.4826 0.00802 0.00277 -0.0829 0.7192 1.0000 1.000 0.5302 0.00813 0.00273 -0.0812 0.6983 1.0000 1.500 0.5784 0.00827 0.00272 -0.0795 0.6772 1.0000 2.000 0.6270 0.00846 0.00276 -0.0779 0.6563 1.0000 2.500 0.6756 0.00866 0.00289 -0.0764 0.6336 1.0000 3.000 0.7242 0.00891 0.00302 -0.0749 0.6109 1.0000 3.500 0.7725 0.00918 0.00324 -0.0733 0.5859 1.0000 4.000 0.8206 0.00950 0.00346 -0.0718 0.5614 1.0000 4.500 0.8684 0.00983 0.00379 -0.0702 0.5355 1.0000 5.000 0.9156 0.01023 0.00413 -0.0685 0.5088 1.0000 5.500 0.9620 0.01067 0.00455 -0.0668 0.4798 1.0000 6.000 1.0079 0.01115 0.00502 -0.0650 0.4497 1.0000 6.500 1.0522 0.01171 0.00556 -0.0629 0.4169 1.0000 7.000 1.0950 0.01236 0.00620 -0.0607 0.3827 1.0000 7.500 1.1362 0.01307 0.00691 -0.0583 0.3458 1.0000 8.000 1.1728 0.01399 0.00774 -0.0553 0.3019 1.0000 8.500 1.2050 0.01511 0.00875 -0.0517 0.2501 1.0000 9.000 1.2287 0.01661 0.00999 -0.0469 0.1903 1.0000 9.500 1.2423 0.01838 0.01146 -0.0407 0.1323 1.0000 10.000 1.2546 0.02041 0.01329 -0.0350 0.0884 1.0000 10.500 1.2565 0.02337 0.01597 -0.0290 0.0403 1.0000 11.000 1.2403 0.02813 0.02066 -0.0221 0.0155 1.0000 11.500 1.2455 0.03172 0.02455 -0.0184 0.0134 1.0000 12.000 1.2454 0.03612 0.02919 -0.0154 0.0120 1.0000 12.500 1.2412 0.04133 0.03462 -0.0132 0.0112 1.0000 13.000 1.2306 0.04763 0.04115 -0.0116 0.0105 1.0000 13.500 1.2213 0.05422 0.04798 -0.0105 0.0101 1.0000 14.000 1.2238 0.05994 0.05396 -0.0106 0.0093 1.0000 14.500 1.2212 0.06662 0.06092 -0.0106 0.0091 1.0000 15.000 1.2173 0.07390 0.06851 -0.0118 0.0086 1.0000 15.500 1.2084 0.08237 0.07732 -0.0137 0.0085 1.0000 16.000 1.1943 0.09219 0.08753 -0.0170 0.0083 1.0000 16.500 1.1745 0.10368 0.09939 -0.0217 0.0084 1.0000 17.000 1.1493 0.11701 0.11308 -0.0283 0.0083 1.0000 17.500 1.1203 0.13214 0.12857 -0.0366 0.0086 1.0000 18.000 1.0891 0.14909 0.14584 -0.0467 0.0087 1.0000 18.500 1.0530 0.16912 0.16611 -0.0589 0.0090 1.0000 19.000 1.0065 0.19537 0.19253 -0.0736 0.0098 1.0000 19.500 0.9776 0.22493 0.22205 -0.0851 0.0162 1.0000