XFOIL Version 6.94 Calculated polar for: FX 61-140 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 0.4517 0.01248 0.00603 -0.0994 0.6033 0.7201 0.500 0.5076 0.01264 0.00610 -0.0996 0.5857 0.7284 1.000 0.5651 0.01272 0.00611 -0.1003 0.5688 0.7356 1.500 0.6180 0.01294 0.00628 -0.0997 0.5540 0.7412 2.000 0.6744 0.01315 0.00640 -0.1001 0.5391 0.7482 2.500 0.7338 0.01324 0.00652 -0.1014 0.5244 0.7547 3.000 0.7860 0.01347 0.00676 -0.1007 0.5110 0.7599 3.500 0.8410 0.01368 0.00702 -0.1008 0.4981 0.7658 4.000 0.8998 0.01395 0.00736 -0.1020 0.4848 0.7727 4.500 0.9544 0.01424 0.00764 -0.1020 0.4717 0.7775 5.000 1.0055 0.01432 0.00788 -0.1012 0.4547 0.7827 5.500 1.0561 0.01445 0.00800 -0.1005 0.4282 0.7890 6.000 1.1108 0.01464 0.00829 -0.1008 0.4047 0.7942 6.500 1.1556 0.01481 0.00846 -0.0989 0.3627 0.7988 7.000 1.2006 0.01535 0.00897 -0.0973 0.3157 0.8046 7.500 1.2385 0.01668 0.00992 -0.0950 0.2300 0.8100 8.000 1.2619 0.01926 0.01185 -0.0910 0.1134 0.8156 8.500 1.2692 0.02221 0.01427 -0.0843 0.0301 0.8207 9.000 1.2778 0.02457 0.01661 -0.0776 0.0069 0.8263 9.500 1.2922 0.02690 0.01915 -0.0726 0.0049 0.8328 10.000 1.3022 0.02948 0.02204 -0.0677 0.0043 0.8383 10.500 1.3054 0.03289 0.02576 -0.0635 0.0040 0.8442 11.000 1.3040 0.03750 0.03065 -0.0608 0.0038 0.8506 11.500 1.2977 0.04336 0.03681 -0.0596 0.0037 0.8572 12.000 1.2877 0.05032 0.04408 -0.0595 0.0036 0.8636 12.500 1.2774 0.05822 0.05224 -0.0607 0.0035 0.8696 13.000 1.2693 0.06642 0.06070 -0.0625 0.0035 0.8751 13.500 1.2636 0.07444 0.06898 -0.0641 0.0035 0.8810 14.000 1.2627 0.08230 0.07710 -0.0660 0.0035 0.8877 14.500 1.2640 0.09024 0.08532 -0.0681 0.0035 0.8952 15.000 1.2624 0.09852 0.09394 -0.0705 0.0035 0.9048 15.500 1.2569 0.10790 0.10371 -0.0740 0.0036 0.9168 17.000 1.1952 0.14893 0.14623 -0.0961 0.0041 1.0000 17.500 1.1685 0.16713 0.16482 -0.1088 0.0043 1.0000 18.000 1.1397 0.18767 0.18567 -0.1231 0.0045 1.0000 18.500 1.1079 0.21261 0.21080 -0.1389 0.0049 1.0000