XFOIL Version 6.94 Calculated polar for: GOE 758 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4804 0.00943 0.00309 -0.0924 0.5730 0.5337 0.500 0.5293 0.00919 0.00323 -0.0909 0.5639 0.6799 1.500 0.7036 0.00882 0.00335 -0.1039 0.5431 1.0000 2.000 0.7522 0.00890 0.00340 -0.1024 0.5340 1.0000 2.500 0.8010 0.00907 0.00346 -0.1010 0.5234 1.0000 3.000 0.8501 0.00922 0.00359 -0.0996 0.5120 1.0000 3.500 0.8940 0.00930 0.00350 -0.0971 0.4822 1.0000 4.000 0.9376 0.00957 0.00360 -0.0947 0.4498 1.0000 4.500 0.9768 0.01011 0.00385 -0.0916 0.4013 1.0000 5.000 1.0162 0.01074 0.00425 -0.0887 0.3614 1.0000 5.500 1.0488 0.01169 0.00486 -0.0847 0.3069 1.0000 6.000 1.0820 0.01259 0.00552 -0.0809 0.2628 1.0000 6.500 1.0764 0.01484 0.00703 -0.0707 0.1458 1.0000 7.000 1.0574 0.01769 0.00933 -0.0592 0.0284 1.0000 7.500 1.0769 0.01922 0.01082 -0.0543 0.0040 1.0000 8.000 1.1043 0.02049 0.01217 -0.0510 0.0038 1.0000 8.500 1.1299 0.02201 0.01379 -0.0478 0.0038 1.0000 9.000 1.1535 0.02383 0.01572 -0.0448 0.0038 1.0000 9.500 1.1746 0.02600 0.01802 -0.0421 0.0038 1.0000 10.000 1.1928 0.02860 0.02077 -0.0397 0.0039 1.0000 10.500 1.2078 0.03171 0.02404 -0.0376 0.0040 1.0000 11.000 1.2190 0.03543 0.02793 -0.0359 0.0042 1.0000 11.500 1.2262 0.03978 0.03246 -0.0345 0.0043 1.0000 12.000 1.2279 0.04492 0.03780 -0.0335 0.0044 1.0000 12.500 1.2242 0.05081 0.04387 -0.0328 0.0045 1.0000 13.000 1.2126 0.05788 0.05112 -0.0324 0.0046 1.0000 13.500 1.2077 0.06444 0.05785 -0.0325 0.0047 1.0000 14.000 1.2109 0.07022 0.06378 -0.0327 0.0049 1.0000 14.500 1.2080 0.07697 0.07069 -0.0332 0.0052 1.0000 15.000 1.2012 0.08438 0.07827 -0.0340 0.0054 1.0000 15.500 1.1945 0.09189 0.08593 -0.0350 0.0057 1.0000 16.000 1.1903 0.09893 0.09308 -0.0359 0.0060 1.0000 16.500 1.1947 0.10416 0.09830 -0.0358 0.0062 1.0000 17.000 1.2043 0.11006 0.10442 -0.0374 0.0068 1.0000 17.500 1.2228 0.11302 0.10748 -0.0363 0.0078 1.0000 18.000 1.2446 0.11606 0.11070 -0.0356 0.0089 1.0000 18.500 1.0887 0.12946 0.12517 -0.0497 0.0085 1.0000