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 = 0.012 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1856 0.04776 0.03213 0.0084 0.9993 0.7826 -2.750 -0.1433 0.04667 0.03132 0.0045 0.9993 0.8334 -2.500 -0.0560 0.04559 0.03045 -0.0112 0.9993 1.0007 -2.250 -0.0398 0.04470 0.02900 -0.0151 0.9993 1.0007 -2.000 -0.0060 0.04492 0.02838 -0.0203 0.9993 1.0007 -1.750 0.0256 0.04553 0.02822 -0.0231 0.9993 1.0007 -1.500 0.0530 0.04625 0.02832 -0.0245 0.9993 1.0007 -1.250 0.0773 0.04703 0.02859 -0.0250 0.9993 1.0007 -1.000 0.0996 0.04786 0.02901 -0.0250 0.9993 1.0007 -0.750 0.1204 0.04874 0.02957 -0.0248 0.9993 1.0007 -0.500 0.1398 0.04971 0.03027 -0.0245 0.9993 1.0007 -0.250 0.1581 0.05075 0.03111 -0.0241 0.9993 1.0007 0.000 0.1753 0.05191 0.03210 -0.0237 0.9993 1.0007 0.250 0.1912 0.05320 0.03328 -0.0234 0.9993 1.0007 0.500 0.2057 0.05466 0.03467 -0.0231 0.9993 1.0007 0.750 0.2185 0.05634 0.03630 -0.0230 0.9993 1.0007 1.000 0.2292 0.05829 0.03825 -0.0230 0.9993 1.0007 1.250 0.2375 0.06058 0.04056 -0.0232 0.9993 1.0007 1.500 0.2436 0.06324 0.04324 -0.0238 0.9993 1.0007 1.750 0.2481 0.06620 0.04622 -0.0246 0.9993 1.0007 2.000 0.2523 0.06928 0.04930 -0.0255 0.9993 1.0007 2.250 0.2574 0.07235 0.05233 -0.0266 0.9993 1.0007 2.500 0.2637 0.07533 0.05527 -0.0276 0.9993 1.0007 2.750 0.2712 0.07822 0.05812 -0.0286 0.9993 1.0007 3.000 0.2796 0.08103 0.06087 -0.0295 0.9993 1.0007 3.250 0.2888 0.08379 0.06356 -0.0305 0.9993 1.0007 3.500 0.2986 0.08650 0.06621 -0.0314 0.9993 1.0007 3.750 0.3088 0.08918 0.06883 -0.0323 0.9993 1.0007 4.000 0.3194 0.09184 0.07143 -0.0332 0.9993 1.0007 4.250 0.3303 0.09449 0.07402 -0.0341 0.9993 1.0007 4.500 0.3414 0.09713 0.07664 -0.0350 0.9993 1.0007 4.750 0.3526 0.09977 0.07924 -0.0358 0.9993 1.0007 5.000 0.3640 0.10242 0.08185 -0.0367 0.9993 1.0007