XFOIL Version 6.96 Calculated polar for: FX60-100 10.0% smoothed 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.500 -0.2974 0.08509 0.08171 -0.0400 1.0000 0.0182 -9.250 -0.3744 0.09103 0.08742 -0.0395 1.0000 0.0185 -9.000 -0.3748 0.08786 0.08430 -0.0399 1.0000 0.0179 -8.750 -0.3778 0.08433 0.08080 -0.0405 1.0000 0.0172 -8.250 -0.4206 0.06939 0.06604 -0.0441 1.0000 0.0141 -8.000 -0.4405 0.06689 0.06364 -0.0418 1.0000 0.0140 -7.750 -0.4354 0.05735 0.05405 -0.0547 0.9928 0.0137 -7.500 -0.4109 0.04530 0.04154 -0.0776 0.9831 0.0134 -7.250 -0.3878 0.03876 0.03453 -0.0866 0.9755 0.0132 -7.000 -0.3566 0.03327 0.02846 -0.0936 0.9712 0.0131 -6.750 -0.3246 0.02912 0.02375 -0.0980 0.9673 0.0131 -6.500 -0.2939 0.02604 0.02016 -0.1007 0.9624 0.0133 -6.250 -0.2595 0.02353 0.01716 -0.1032 0.9592 0.0137 -6.000 -0.2237 0.02172 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0.0116 1.0000 13.500 1.4726 0.05445 0.04850 -0.0635 0.0112 1.0000 13.750 1.4652 0.05852 0.05273 -0.0638 0.0108 1.0000 14.000 1.4548 0.06322 0.05763 -0.0645 0.0105 1.0000 14.250 1.4454 0.06808 0.06266 -0.0657 0.0103 1.0000 14.500 1.4362 0.07316 0.06795 -0.0672 0.0101 1.0000 14.750 1.4258 0.07873 0.07372 -0.0693 0.0099 1.0000 15.000 1.4142 0.08480 0.07999 -0.0718 0.0098 1.0000 15.250 1.4014 0.09136 0.08675 -0.0748 0.0096 1.0000 15.500 1.3879 0.09836 0.09395 -0.0782 0.0095 1.0000 15.750 1.3735 0.10582 0.10159 -0.0821 0.0094 1.0000 16.000 1.3585 0.11369 0.10965 -0.0864 0.0094 1.0000 16.250 1.3435 0.12185 0.11799 -0.0911 0.0094 1.0000 16.500 1.3278 0.13041 0.12672 -0.0961 0.0093 1.0000 16.750 1.3124 0.13921 0.13568 -0.1014 0.0093 1.0000 17.000 1.2971 0.14825 0.14487 -0.1070 0.0094 1.0000 17.250 1.2820 0.15756 0.15434 -0.1129 0.0094 1.0000 17.500 1.2669 0.16721 0.16412 -0.1190 0.0094 1.0000 17.750 1.2514 0.17735 0.17439 -0.1255 0.0095 1.0000 18.000 1.2348 0.18831 0.18544 -0.1326 0.0096 1.0000 18.250 1.2143 0.20141 0.19864 -0.1408 0.0097 1.0000