XFOIL Version 6.94 Calculated polar for: FX 60-100 AIRFOIL 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 0.5115 0.00887 0.00331 -0.1202 0.8265 0.5981 0.500 0.5662 0.00876 0.00317 -0.1192 0.8013 0.6204 1.000 0.6203 0.00868 0.00312 -0.1182 0.7716 0.6468 1.500 0.6741 0.00866 0.00309 -0.1173 0.7381 0.6749 2.000 0.7276 0.00870 0.00313 -0.1163 0.7018 0.7054 2.500 0.7795 0.00881 0.00326 -0.1150 0.6576 0.7451 3.000 0.8278 0.00887 0.00344 -0.1130 0.6140 0.8155 4.000 0.9265 0.00956 0.00393 -0.1099 0.5183 1.0000 4.500 0.9780 0.01015 0.00438 -0.1091 0.4703 1.0000 5.000 1.0273 0.01088 0.00492 -0.1079 0.4123 1.0000 5.500 1.0737 0.01185 0.00560 -0.1064 0.3365 1.0000 6.500 1.1571 0.01485 0.00763 -0.1024 0.1571 1.0000 7.000 1.2000 0.01620 0.00879 -0.1006 0.1164 1.0000 7.500 1.2417 0.01759 0.01001 -0.0987 0.0838 1.0000 8.000 1.2836 0.01886 0.01124 -0.0967 0.0639 1.0000 8.500 1.3218 0.02034 0.01277 -0.0942 0.0530 1.0000 9.000 1.3584 0.02178 0.01430 -0.0915 0.0438 1.0000 9.500 1.3952 0.02303 0.01571 -0.0888 0.0364 1.0000 10.000 1.4255 0.02443 0.01713 -0.0852 0.0243 1.0000 10.500 1.4355 0.02724 0.01986 -0.0792 0.0060 1.0000 11.000 1.4437 0.03042 0.02332 -0.0736 0.0045 1.0000 11.500 1.4540 0.03363 0.02687 -0.0691 0.0040 1.0000 12.000 1.4587 0.03757 0.03116 -0.0651 0.0037 1.0000 12.500 1.4571 0.04248 0.03642 -0.0620 0.0035 1.0000 13.000 1.4492 0.04861 0.04290 -0.0602 0.0034 1.0000 13.500 1.4348 0.05635 0.05099 -0.0602 0.0033 1.0000 14.000 1.4152 0.06596 0.06096 -0.0624 0.0032 1.0000 14.500 1.3919 0.07759 0.07294 -0.0668 0.0032 1.0000 15.000 1.3662 0.09110 0.08680 -0.0734 0.0032 1.0000 15.500 1.3385 0.10637 0.10242 -0.0816 0.0032 1.0000 16.000 1.3112 0.12269 0.11907 -0.0910 0.0033 1.0000 16.500 1.2850 0.13955 0.13622 -0.1011 0.0033 1.0000 17.000 1.2628 0.15591 0.15284 -0.1111 0.0034 1.0000 17.500 1.2443 0.17178 0.16894 -0.1211 0.0035 1.0000 18.000 1.2285 0.18737 0.18473 -0.1310 0.0036 1.0000 18.500 1.2128 0.20378 0.20133 -0.1414 0.0038 1.0000 19.000 1.1872 0.22576 0.22347 -0.1544 0.0041 1.0000