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 = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4283 0.00641 0.00187 -0.0860 0.6930 1.0000 0.500 0.4781 0.00657 0.00184 -0.0846 0.6735 1.0000 1.000 0.5285 0.00674 0.00185 -0.0834 0.6542 1.0000 1.500 0.5793 0.00694 0.00189 -0.0822 0.6350 1.0000 2.000 0.6308 0.00712 0.00199 -0.0812 0.6150 1.0000 2.500 0.6825 0.00732 0.00210 -0.0802 0.5935 1.0000 3.000 0.7341 0.00755 0.00226 -0.0793 0.5707 1.0000 3.500 0.7858 0.00780 0.00244 -0.0784 0.5455 1.0000 4.000 0.8368 0.00811 0.00268 -0.0774 0.5180 1.0000 4.500 0.8877 0.00843 0.00295 -0.0764 0.4870 1.0000 5.000 0.9375 0.00885 0.00330 -0.0753 0.4511 1.0000 5.500 0.9865 0.00935 0.00371 -0.0741 0.4092 1.0000 6.000 1.0325 0.01007 0.00424 -0.0725 0.3541 1.0000 6.500 1.0770 0.01094 0.00488 -0.0707 0.2942 1.0000 7.000 1.1199 0.01196 0.00565 -0.0688 0.2364 1.0000 7.500 1.1622 0.01300 0.00653 -0.0669 0.1853 1.0000 8.000 1.2017 0.01423 0.00754 -0.0645 0.1344 1.0000 8.500 1.2358 0.01582 0.00884 -0.0615 0.0786 1.0000 9.000 1.2564 0.01831 0.01094 -0.0564 0.0216 1.0000 9.500 1.2851 0.01985 0.01263 -0.0523 0.0174 1.0000 10.000 1.3045 0.02163 0.01458 -0.0469 0.0155 1.0000 10.500 1.3132 0.02416 0.01733 -0.0408 0.0144 1.0000 11.000 1.3172 0.02727 0.02071 -0.0353 0.0139 1.0000 11.500 1.3234 0.03067 0.02434 -0.0313 0.0136 1.0000 12.000 1.3282 0.03465 0.02856 -0.0282 0.0132 1.0000 12.500 1.3334 0.03900 0.03315 -0.0260 0.0124 1.0000 13.000 1.3349 0.04415 0.03855 -0.0243 0.0121 1.0000 13.500 1.3356 0.04974 0.04440 -0.0233 0.0118 1.0000 14.000 1.3341 0.05594 0.05092 -0.0228 0.0116 1.0000 14.500 1.3288 0.06304 0.05833 -0.0234 0.0113 1.0000 15.000 1.3182 0.07135 0.06695 -0.0250 0.0111 1.0000 15.500 1.3034 0.08093 0.07687 -0.0280 0.0110 1.0000 16.000 1.2842 0.09193 0.08818 -0.0327 0.0108 1.0000 16.500 1.2642 0.10374 0.10024 -0.0385 0.0103 1.0000 17.000 1.2375 0.11791 0.11474 -0.0463 0.0103 1.0000 17.500 1.2059 0.13452 0.13170 -0.0563 0.0104 1.0000