XFOIL Version 6.94 Calculated polar for: S3025 9.38% 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 0.4297 0.00761 0.00252 -0.0868 0.7312 1.0000 0.500 0.4793 0.00779 0.00249 -0.0853 0.7102 1.0000 1.000 0.5296 0.00799 0.00250 -0.0840 0.6898 1.0000 1.500 0.5805 0.00821 0.00255 -0.0828 0.6699 1.0000 2.000 0.6318 0.00843 0.00266 -0.0817 0.6496 1.0000 2.500 0.6832 0.00865 0.00280 -0.0807 0.6278 1.0000 3.000 0.7346 0.00889 0.00297 -0.0796 0.6055 1.0000 3.500 0.7858 0.00915 0.00316 -0.0786 0.5814 1.0000 4.000 0.8365 0.00942 0.00341 -0.0774 0.5541 1.0000 4.500 0.8868 0.00973 0.00370 -0.0763 0.5248 1.0000 5.000 0.9363 0.01011 0.00405 -0.0750 0.4917 1.0000 5.500 0.9843 0.01059 0.00446 -0.0735 0.4535 1.0000 6.000 1.0312 0.01116 0.00499 -0.0719 0.4099 1.0000 6.500 1.0745 0.01197 0.00561 -0.0698 0.3542 1.0000 7.000 1.1166 0.01292 0.00640 -0.0677 0.2974 1.0000 7.500 1.1556 0.01410 0.00736 -0.0652 0.2365 1.0000 8.000 1.1945 0.01530 0.00842 -0.0628 0.1867 1.0000 8.500 1.2295 0.01674 0.00967 -0.0599 0.1346 1.0000 9.000 1.2555 0.01878 0.01139 -0.0558 0.0716 1.0000 10.000 1.2807 0.02376 0.01627 -0.0435 0.0224 1.0000 10.500 1.2869 0.02665 0.01936 -0.0378 0.0202 1.0000 11.000 1.2883 0.03029 0.02325 -0.0327 0.0192 1.0000 11.500 1.2941 0.03409 0.02732 -0.0292 0.0186 1.0000 12.000 1.2995 0.03842 0.03190 -0.0264 0.0180 1.0000 12.500 1.3057 0.04312 0.03686 -0.0242 0.0173 1.0000 13.000 1.3119 0.04811 0.04212 -0.0226 0.0166 1.0000 13.500 1.3152 0.05354 0.04779 -0.0219 0.0156 1.0000 14.000 1.3153 0.05989 0.05446 -0.0215 0.0153 1.0000 14.500 1.3090 0.06739 0.06232 -0.0220 0.0150 1.0000 15.000 1.2948 0.07647 0.07179 -0.0239 0.0148 1.0000 15.500 1.2733 0.08724 0.08299 -0.0277 0.0149 1.0000 16.000 1.2440 0.10042 0.09660 -0.0339 0.0151 1.0000 16.500 1.2075 0.11638 0.11299 -0.0430 0.0153 1.0000 17.000 1.1558 0.13815 0.13523 -0.0567 0.0159 1.0000 17.500 1.0510 0.18172 0.17916 -0.0837 0.0181 1.0000