XFOIL Version 6.94 Calculated polar for: SG6051 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 0.3854 0.00947 0.00450 -0.0867 0.7945 1.0000 0.500 0.4392 0.00951 0.00441 -0.0865 0.7846 1.0000 1.000 0.4938 0.00969 0.00445 -0.0864 0.7741 1.0000 1.500 0.5497 0.00976 0.00451 -0.0867 0.7625 1.0000 2.000 0.6057 0.00974 0.00443 -0.0867 0.7501 1.0000 2.500 0.6618 0.00991 0.00456 -0.0870 0.7373 1.0000 3.000 0.7180 0.00989 0.00453 -0.0870 0.7216 1.0000 3.500 0.7741 0.00999 0.00459 -0.0871 0.7052 1.0000 4.000 0.8300 0.00999 0.00461 -0.0871 0.6856 1.0000 4.500 0.8853 0.01008 0.00487 -0.0870 0.6627 1.0000 5.000 0.9398 0.01019 0.00496 -0.0867 0.6337 1.0000 5.500 0.9929 0.01041 0.00516 -0.0862 0.5957 1.0000 6.000 1.0411 0.01092 0.00544 -0.0848 0.5247 1.0000 6.500 1.0830 0.01200 0.00619 -0.0826 0.4309 1.0000 7.000 1.1154 0.01377 0.00739 -0.0791 0.3111 1.0000 7.500 1.1410 0.01594 0.00895 -0.0749 0.1993 1.0000 8.000 1.1620 0.01821 0.01073 -0.0699 0.1114 1.0000 8.500 1.1759 0.02050 0.01277 -0.0635 0.0673 1.0000 9.000 1.1916 0.02285 0.01517 -0.0579 0.0527 1.0000 9.500 1.2095 0.02533 0.01775 -0.0533 0.0449 1.0000 10.000 1.2269 0.02806 0.02074 -0.0491 0.0393 1.0000 10.500 1.2507 0.03030 0.02312 -0.0462 0.0330 1.0000 12.500 1.2897 0.04623 0.03993 -0.0315 0.0132 1.0000 13.000 1.2994 0.05019 0.04405 -0.0299 0.0115 1.0000 13.500 1.3001 0.05552 0.04963 -0.0279 0.0105 1.0000 14.000 1.2905 0.06253 0.05704 -0.0258 0.0100 1.0000 14.500 1.2743 0.07054 0.06555 -0.0247 0.0099 1.0000 15.000 1.2492 0.08056 0.07601 -0.0256 0.0098 1.0000 15.500 1.2192 0.09234 0.08823 -0.0289 0.0097 1.0000 16.000 1.1875 0.10567 0.10196 -0.0347 0.0097 1.0000 16.500 1.1553 0.12054 0.11718 -0.0429 0.0097 1.0000 17.000 1.1237 0.13705 0.13401 -0.0531 0.0099 1.0000 17.500 1.0793 0.15887 0.15611 -0.0672 0.0102 1.0000 19.000 0.9727 0.24144 0.23864 -0.1015 0.0163 1.0000 21.000 0.9945 0.29149 0.28865 -0.1196 0.0146 1.0000 21.500 1.0009 0.30277 0.29995 -0.1234 0.0129 1.0000 22.000 1.0067 0.31347 0.31066 -0.1266 0.0118 1.0000 22.500 1.0117 0.32378 0.32098 -0.1296 0.0111 1.0000 23.000 1.0158 0.33351 0.33073 -0.1319 0.0104 1.0000 23.500 1.0183 0.34282 0.34006 -0.1335 0.0099 1.0000