XFOIL Version 6.94 Calculated polar for: Eif385mod 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.026 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.0947 0.04126 0.02714 -0.0259 0.9993 0.4292 -2.750 -0.0673 0.04099 0.02668 -0.0265 0.9993 0.4342 -2.500 -0.0407 0.04072 0.02638 -0.0268 0.9993 0.4428 -2.250 -0.0146 0.04055 0.02621 -0.0270 0.9993 0.4532 -2.000 0.0117 0.04057 0.02619 -0.0273 0.9993 0.4624 -1.750 0.0367 0.04052 0.02629 -0.0274 0.9993 0.4730 -1.500 0.0609 0.04056 0.02653 -0.0274 0.9993 0.4915 -1.250 0.0843 0.04057 0.02692 -0.0273 0.9993 0.5181 -1.000 0.1068 0.04049 0.02746 -0.0270 0.9993 0.5626 -0.750 0.1143 0.03945 0.02775 -0.0240 0.9993 1.0007 -0.500 0.1369 0.04058 0.02856 -0.0245 0.9993 1.0007 -0.250 0.1567 0.04181 0.02956 -0.0246 0.9993 1.0007 0.000 0.1743 0.04320 0.03079 -0.0246 0.9993 1.0007 0.250 0.1893 0.04485 0.03235 -0.0246 0.9993 1.0007 0.500 0.2005 0.04693 0.03441 -0.0248 0.9993 1.0007 0.750 0.2465 0.04957 0.03701 -0.0329 0.9799 1.0007 1.000 0.3944 0.05002 0.03724 -0.0567 0.8909 1.0007 1.250 0.5045 0.04873 0.03584 -0.0704 0.8232 1.0007 1.500 0.5734 0.04783 0.03485 -0.0760 0.7751 1.0007 1.750 0.6253 0.04738 0.03427 -0.0787 0.7409 1.0007 2.000 0.6646 0.04775 0.03452 -0.0799 0.7148 1.0007 2.250 0.6963 0.04885 0.03555 -0.0808 0.6946 1.0007 2.500 0.7277 0.05007 0.03670 -0.0818 0.6787 1.0007 2.750 0.7476 0.05228 0.03888 -0.0820 0.6651 1.0007 3.000 0.7562 0.05543 0.04202 -0.0814 0.6532 1.0007 3.250 0.7601 0.05896 0.04558 -0.0805 0.6430 1.0007 3.500 0.7803 0.06123 0.04783 -0.0808 0.6339 1.0007 3.750 0.7629 0.06645 0.05307 -0.0786 0.6269 1.0007 4.000 0.7862 0.06878 0.05540 -0.0794 0.6209 1.0007 4.250 0.7573 0.07515 0.06176 -0.0771 0.6205 1.0007 4.500 0.7294 0.08136 0.06797 -0.0751 0.6228 1.0007 4.750 0.6990 0.08752 0.07410 -0.0733 0.6290 1.0007 5.000 0.6989 0.09194 0.07853 -0.0738 0.6337 1.0007