XFOIL Version 6.94 Calculated polar for: S4062-095-87 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 0.4714 0.00878 0.00405 -0.1049 0.7899 1.0000 0.500 0.5263 0.00886 0.00397 -0.1045 0.7796 1.0000 1.000 0.5816 0.00883 0.00376 -0.1039 0.7675 1.0000 1.500 0.6361 0.00882 0.00366 -0.1033 0.7527 1.0000 2.000 0.6908 0.00887 0.00365 -0.1029 0.7383 1.0000 2.500 0.7456 0.00893 0.00368 -0.1024 0.7235 1.0000 3.000 0.8002 0.00900 0.00373 -0.1019 0.7074 1.0000 3.500 0.8546 0.00908 0.00380 -0.1014 0.6894 1.0000 4.000 0.9086 0.00918 0.00388 -0.1007 0.6686 1.0000 4.500 0.9611 0.00932 0.00407 -0.0999 0.6411 1.0000 5.000 1.0126 0.00953 0.00429 -0.0988 0.6065 1.0000 5.500 1.0613 0.00992 0.00459 -0.0973 0.5559 1.0000 6.000 1.1026 0.01080 0.00513 -0.0947 0.4667 1.0000 6.500 1.1362 0.01229 0.00610 -0.0912 0.3646 1.0000 7.000 1.1712 0.01370 0.00723 -0.0881 0.2940 1.0000 7.500 1.2042 0.01515 0.00841 -0.0848 0.2338 1.0000 8.000 1.2360 0.01656 0.00962 -0.0815 0.1823 1.0000 8.500 1.2622 0.01805 0.01095 -0.0772 0.1399 1.0000 9.000 1.2868 0.01964 0.01246 -0.0729 0.1046 1.0000 9.500 1.3084 0.02159 0.01430 -0.0686 0.0730 1.0000 10.000 1.3232 0.02421 0.01678 -0.0640 0.0449 1.0000 10.500 1.3298 0.02770 0.02035 -0.0588 0.0313 1.0000 11.000 1.3453 0.03065 0.02351 -0.0551 0.0270 1.0000 11.500 1.3494 0.03485 0.02785 -0.0511 0.0241 1.0000 12.000 1.3613 0.03868 0.03194 -0.0481 0.0223 1.0000 12.500 1.3739 0.04268 0.03620 -0.0455 0.0207 1.0000 13.000 1.3842 0.04713 0.04092 -0.0433 0.0195 1.0000 13.500 1.3915 0.05215 0.04615 -0.0416 0.0184 1.0000 14.000 1.3885 0.05962 0.05400 -0.0398 0.0171 1.0000 14.500 1.3836 0.06624 0.06103 -0.0395 0.0165 1.0000 15.000 1.3707 0.07483 0.07007 -0.0404 0.0160 1.0000 15.500 1.3493 0.08535 0.08104 -0.0430 0.0157 1.0000 16.000 1.3206 0.09809 0.09423 -0.0480 0.0156 1.0000 16.500 1.2853 0.11347 0.11004 -0.0560 0.0156 1.0000 17.000 1.2448 0.13187 0.12883 -0.0672 0.0158 1.0000 17.500 1.1982 0.15411 0.15141 -0.0818 0.0163 1.0000