XFOIL Version 6.94 Calculated polar for: FX60-100 10.0% smoothed 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 0.5127 0.00723 0.00206 -0.1195 0.7924 0.5587 0.500 0.5682 0.00727 0.00205 -0.1190 0.7665 0.5841 1.000 0.6233 0.00730 0.00210 -0.1185 0.7376 0.6106 1.500 0.6779 0.00740 0.00218 -0.1179 0.7046 0.6403 2.000 0.7317 0.00756 0.00232 -0.1171 0.6668 0.6744 2.500 0.7841 0.00779 0.00249 -0.1161 0.6171 0.7155 3.000 0.8353 0.00803 0.00275 -0.1149 0.5671 0.7720 4.000 0.9321 0.00856 0.00329 -0.1114 0.4676 1.0000 4.500 0.9838 0.00920 0.00372 -0.1107 0.4134 1.0000 5.000 1.0337 0.01002 0.00425 -0.1098 0.3471 1.0000 5.500 1.0823 0.01098 0.00492 -0.1087 0.2759 1.0000 6.000 1.1281 0.01227 0.00579 -0.1073 0.1940 1.0000 6.500 1.1731 0.01361 0.00683 -0.1058 0.1346 1.0000 7.000 1.2186 0.01485 0.00794 -0.1043 0.1052 1.0000 7.500 1.2640 0.01600 0.00911 -0.1027 0.0894 1.0000 8.000 1.3075 0.01724 0.01036 -0.1009 0.0762 1.0000 8.500 1.3529 0.01819 0.01138 -0.0993 0.0660 1.0000 9.000 1.3966 0.01917 0.01249 -0.0976 0.0561 1.0000 9.500 1.4378 0.02029 0.01367 -0.0956 0.0459 1.0000 10.000 1.4760 0.02155 0.01497 -0.0932 0.0346 1.0000 10.500 1.5024 0.02350 0.01687 -0.0891 0.0214 1.0000 11.000 1.5149 0.02610 0.01959 -0.0831 0.0150 1.0000 11.500 1.5249 0.02899 0.02276 -0.0776 0.0124 1.0000 12.000 1.5313 0.03242 0.02639 -0.0729 0.0106 1.0000 12.500 1.5216 0.03772 0.03199 -0.0681 0.0095 1.0000 13.000 1.5229 0.04258 0.03716 -0.0655 0.0090 1.0000 13.500 1.5176 0.04872 0.04361 -0.0639 0.0086 1.0000 14.000 1.5073 0.05619 0.05140 -0.0639 0.0082 1.0000 14.500 1.4930 0.06506 0.06059 -0.0655 0.0079 1.0000 15.000 1.4744 0.07558 0.07143 -0.0689 0.0077 1.0000 15.500 1.4521 0.08782 0.08400 -0.0740 0.0076 1.0000 16.000 1.4265 0.10169 0.09819 -0.0809 0.0075 1.0000 16.500 1.3981 0.11715 0.11398 -0.0893 0.0074 1.0000 17.000 1.3685 0.13381 0.13097 -0.0990 0.0074 1.0000 17.500 1.3364 0.15213 0.14962 -0.1103 0.0075 1.0000 18.000 1.3011 0.17266 0.17048 -0.1235 0.0077 1.0000