XFOIL Version 6.94 Calculated polar for: SG6042 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 0.4903 0.00872 0.00435 -0.1135 0.8556 0.9365 0.500 0.5752 0.00847 0.00401 -0.1192 0.8425 1.0000 1.000 0.6305 0.00842 0.00382 -0.1190 0.8259 1.0000 1.500 0.6857 0.00839 0.00366 -0.1185 0.8067 1.0000 2.000 0.7404 0.00837 0.00354 -0.1178 0.7851 1.0000 2.500 0.7924 0.00842 0.00350 -0.1166 0.7597 1.0000 3.000 0.8441 0.00850 0.00347 -0.1153 0.7293 1.0000 3.500 0.8927 0.00868 0.00355 -0.1134 0.6899 1.0000 4.000 0.9402 0.00901 0.00371 -0.1114 0.6442 1.0000 4.500 0.9837 0.00952 0.00401 -0.1086 0.5853 1.0000 5.000 1.0224 0.01027 0.00444 -0.1051 0.5131 1.0000 5.500 1.0565 0.01127 0.00506 -0.1009 0.4327 1.0000 6.000 1.0893 0.01240 0.00582 -0.0967 0.3536 1.0000 6.500 1.1214 0.01362 0.00671 -0.0926 0.2828 1.0000 7.000 1.1523 0.01487 0.00767 -0.0884 0.2253 1.0000 7.500 1.1829 0.01615 0.00875 -0.0842 0.1797 1.0000 8.000 1.2139 0.01746 0.00994 -0.0802 0.1477 1.0000 8.500 1.2445 0.01884 0.01126 -0.0763 0.1237 1.0000 9.000 1.2745 0.02026 0.01270 -0.0725 0.1052 1.0000 9.500 1.3027 0.02184 0.01432 -0.0686 0.0911 1.0000 10.000 1.3277 0.02369 0.01622 -0.0645 0.0801 1.0000 10.500 1.3515 0.02567 0.01825 -0.0606 0.0702 1.0000 11.000 1.3781 0.02750 0.02028 -0.0573 0.0627 1.0000 11.500 1.3955 0.03021 0.02308 -0.0533 0.0555 1.0000 12.000 1.4173 0.03251 0.02559 -0.0502 0.0496 1.0000 12.500 1.4284 0.03621 0.02941 -0.0464 0.0446 1.0000 13.000 1.4447 0.03928 0.03275 -0.0436 0.0406 1.0000 13.500 1.4535 0.04323 0.03684 -0.0409 0.0372 1.0000 14.000 1.4605 0.04805 0.04196 -0.0384 0.0348 1.0000 14.500 1.4660 0.05291 0.04717 -0.0366 0.0329 1.0000 15.000 1.4673 0.05848 0.05302 -0.0355 0.0312 1.0000 15.500 1.4651 0.06476 0.05955 -0.0352 0.0299 1.0000 16.000 1.4562 0.07259 0.06767 -0.0358 0.0288 1.0000 16.500 1.4292 0.08390 0.07943 -0.0381 0.0279 1.0000 17.000 1.4045 0.09527 0.09123 -0.0427 0.0276 1.0000 17.500 1.3725 0.10909 0.10548 -0.0498 0.0273 1.0000 18.000 1.3304 0.12636 0.12316 -0.0601 0.0272 1.0000 18.500 1.2698 0.14982 0.14702 -0.0757 0.0275 1.0000