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 = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.500 -0.2994 0.09393 0.09238 -0.0383 1.0000 0.0108 -10.250 -0.2984 0.09061 0.08907 -0.0387 1.0000 0.0109 -10.000 -0.2977 0.08748 0.08594 -0.0389 1.0000 0.0111 -6.000 -0.1664 0.01299 0.00846 -0.1169 0.9334 0.0094 -5.750 -0.1393 0.01192 0.00725 -0.1168 0.9273 0.0096 -5.500 -0.1119 0.01128 0.00651 -0.1168 0.9207 0.0100 -5.250 -0.0845 0.01026 0.00536 -0.1169 0.9141 0.0105 -5.000 -0.0566 0.00953 0.00457 -0.1171 0.9076 0.0112 -4.750 -0.0285 0.00912 0.00411 -0.1172 0.9007 0.0117 -4.500 -0.0002 0.00875 0.00367 -0.1172 0.8941 0.0123 -4.250 0.0283 0.00840 0.00325 -0.1173 0.8869 0.0130 -4.000 0.0567 0.00819 0.00299 -0.1174 0.8801 0.0139 -3.750 0.0857 0.00771 0.00242 -0.1176 0.8725 0.0161 -3.500 0.1143 0.00749 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0.01112 0.00510 -0.1105 0.1068 1.0000 6.500 1.1899 0.01151 0.00544 -0.1101 0.0950 1.0000 6.750 1.2152 0.01185 0.00576 -0.1097 0.0871 1.0000 7.000 1.2398 0.01225 0.00613 -0.1093 0.0786 1.0000 7.250 1.2648 0.01258 0.00645 -0.1089 0.0728 1.0000 7.500 1.2892 0.01298 0.00684 -0.1084 0.0662 1.0000 7.750 1.3142 0.01330 0.00715 -0.1080 0.0616 1.0000 8.000 1.3378 0.01376 0.00757 -0.1074 0.0550 1.0000 8.250 1.3627 0.01404 0.00789 -0.1069 0.0521 1.0000 8.500 1.3862 0.01446 0.00830 -0.1064 0.0476 1.0000 8.750 1.4098 0.01487 0.00872 -0.1058 0.0435 1.0000 9.000 1.4332 0.01526 0.00913 -0.1051 0.0396 1.0000 9.250 1.4554 0.01578 0.00961 -0.1044 0.0344 1.0000 9.500 1.4776 0.01626 0.01009 -0.1036 0.0298 1.0000 9.750 1.4984 0.01685 0.01067 -0.1026 0.0241 1.0000 10.000 1.5175 0.01760 0.01138 -0.1014 0.0178 1.0000 10.250 1.5355 0.01842 0.01219 -0.1001 0.0129 1.0000 10.500 1.5525 0.01929 0.01308 -0.0986 0.0099 1.0000 10.750 1.5690 0.02015 0.01396 -0.0970 0.0082 1.0000 11.000 1.5841 0.02107 0.01496 -0.0952 0.0070 1.0000 11.250 1.5994 0.02183 0.01580 -0.0934 0.0064 1.0000 11.500 1.6108 0.02268 0.01671 -0.0910 0.0059 1.0000 11.750 1.6184 0.02372 0.01782 -0.0881 0.0055 1.0000 12.000 1.6204 0.02518 0.01942 -0.0846 0.0050 1.0000 12.250 1.6294 0.02619 0.02053 -0.0823 0.0049 1.0000 12.500 1.6374 0.02733 0.02176 -0.0800 0.0048 1.0000 12.750 1.6441 0.02860 0.02314 -0.0778 0.0046 1.0000 13.000 1.6493 0.03006 0.02469 -0.0756 0.0045 1.0000 13.250 1.6539 0.03163 0.02637 -0.0736 0.0044 1.0000 13.500 1.6570 0.03342 0.02827 -0.0717 0.0043 1.0000 13.750 1.6596 0.03534 0.03029 -0.0700 0.0042 1.0000 14.000 1.6607 0.03751 0.03258 -0.0685 0.0041 1.0000 14.250 1.6608 0.03988 0.03506 -0.0672 0.0040 1.0000 14.500 1.6591 0.04259 0.03788 -0.0662 0.0039 1.0000 14.750 1.6561 0.04562 0.04103 -0.0655 0.0038 1.0000 15.000 1.6510 0.04906 0.04460 -0.0652 0.0038 1.0000 15.250 1.6434 0.05305 0.04874 -0.0653 0.0037 1.0000 15.500 1.6341 0.05752 0.05335 -0.0660 0.0036 1.0000 15.750 1.6221 0.06270 0.05868 -0.0672 0.0036 1.0000 16.000 1.6088 0.06847 0.06460 -0.0690 0.0035 1.0000 16.250 1.5936 0.07491 0.07120 -0.0715 0.0035 1.0000 16.500 1.5771 0.08194 0.07838 -0.0746 0.0035 1.0000 16.750 1.5592 0.08961 0.08621 -0.0782 0.0035 1.0000 17.000 1.5405 0.09774 0.09450 -0.0823 0.0035 1.0000 17.250 1.5204 0.10649 0.10340 -0.0869 0.0035 1.0000 17.500 1.5016 0.11520 0.11227 -0.0916 0.0035 1.0000 17.750 1.4833 0.12405 0.12125 -0.0965 0.0035 1.0000