XFOIL Version 6.94 Calculated polar for: SD8000-089-88 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 0.2171 0.00571 0.00194 -0.0487 0.8444 0.8856 0.500 0.2748 0.00561 0.00184 -0.0479 0.8136 0.9570 1.000 0.3570 0.00563 0.00170 -0.0530 0.7708 0.9966 1.500 0.4083 0.00582 0.00165 -0.0518 0.7196 1.0000 2.000 0.4567 0.00614 0.00169 -0.0500 0.6586 1.0000 2.500 0.5061 0.00657 0.00182 -0.0484 0.5878 1.0000 3.000 0.5558 0.00711 0.00203 -0.0471 0.5106 1.0000 3.500 0.6060 0.00770 0.00231 -0.0460 0.4340 1.0000 4.000 0.6561 0.00839 0.00269 -0.0449 0.3578 1.0000 4.500 0.7064 0.00912 0.00312 -0.0440 0.2865 1.0000 5.000 0.7566 0.00988 0.00364 -0.0431 0.2269 1.0000 5.500 0.8071 0.01064 0.00421 -0.0423 0.1800 1.0000 6.000 0.8571 0.01144 0.00486 -0.0413 0.1404 1.0000 6.500 0.9068 0.01227 0.00558 -0.0404 0.1081 1.0000 7.000 0.9556 0.01318 0.00640 -0.0393 0.0837 1.0000 7.500 1.0045 0.01405 0.00730 -0.0382 0.0650 1.0000 8.000 1.0515 0.01512 0.00834 -0.0369 0.0471 1.0000 8.500 1.0931 0.01686 0.01008 -0.0348 0.0319 1.0000 9.000 1.1365 0.01821 0.01155 -0.0330 0.0260 1.0000 10.500 1.2409 0.02431 0.01826 -0.0244 0.0192 1.0000 11.000 1.2540 0.02862 0.02288 -0.0195 0.0175 1.0000 11.500 1.2723 0.03096 0.02551 -0.0148 0.0169 1.0000 12.000 1.2818 0.03400 0.02888 -0.0101 0.0161 1.0000 12.500 1.2865 0.03743 0.03259 -0.0062 0.0151 1.0000 13.000 1.2871 0.04146 0.03687 -0.0037 0.0143 1.0000 13.500 1.2783 0.04727 0.04298 -0.0028 0.0138 1.0000 14.000 1.2618 0.05502 0.05102 -0.0043 0.0133 1.0000 14.500 1.2356 0.06561 0.06194 -0.0090 0.0131 1.0000 15.000 1.2013 0.07937 0.07607 -0.0169 0.0131 1.0000 15.500 1.1631 0.09592 0.09297 -0.0275 0.0132 1.0000