XFOIL Version 6.96 Calculated polar for: FX 60-160 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.500 -0.2808 0.09113 0.08793 -0.0664 0.9848 0.0817 -10.250 -0.2778 0.08530 0.08210 -0.0709 0.9827 0.0857 -10.000 -0.3331 0.07070 0.06750 -0.0839 0.9764 0.0889 -9.750 -0.5241 0.07294 0.06907 -0.0902 0.9706 0.0764 -9.500 -0.4953 0.06550 0.06194 -0.0906 0.9716 0.0792 -9.250 -0.4739 0.06251 0.05893 -0.0932 0.9667 0.0818 -9.000 -0.4725 0.05811 0.05423 -0.0987 0.9563 0.0874 -8.750 -0.4827 0.05321 0.04893 -0.1012 0.9439 0.0923 -8.500 -0.4499 0.05045 0.04626 -0.1037 0.9419 0.0967 -8.250 -0.4627 0.03939 0.03367 -0.1025 0.9288 0.0622 -8.000 -0.4343 0.03556 0.02946 -0.1048 0.9261 0.0615 -7.750 -0.4162 0.03304 0.02662 -0.1042 0.9183 0.0613 -7.500 -0.3868 0.03030 0.02355 -0.1055 0.9142 0.0607 -7.250 -0.3520 0.02818 0.02111 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2.500 0.6878 0.01601 0.00947 -0.1006 0.7068 0.7795 2.750 0.7135 0.01608 0.00955 -0.1005 0.7003 0.7839 3.000 0.7380 0.01603 0.00955 -0.0999 0.6938 0.7874 3.250 0.7698 0.01597 0.00946 -0.1006 0.6892 0.7913 3.500 0.7901 0.01608 0.00967 -0.0994 0.6813 0.7956 3.750 0.8201 0.01604 0.00961 -0.1000 0.6754 0.7996 4.000 0.8432 0.01602 0.00966 -0.0991 0.6677 0.8033 4.250 0.8710 0.01584 0.00948 -0.0990 0.6593 0.8073 4.500 0.8937 0.01576 0.00945 -0.0980 0.6490 0.8115 4.750 0.9220 0.01556 0.00922 -0.0980 0.6392 0.8155 5.000 0.9444 0.01535 0.00905 -0.0967 0.6276 0.8194 5.250 0.9649 0.01525 0.00901 -0.0953 0.6155 0.8237 5.500 0.9882 0.01519 0.00897 -0.0944 0.6041 0.8280 5.750 1.0102 0.01506 0.00886 -0.0932 0.5913 0.8320 6.000 1.0316 0.01498 0.00881 -0.0919 0.5784 0.8365 6.250 1.0503 0.01496 0.00881 -0.0901 0.5631 0.8413 6.500 1.0663 0.01498 0.00886 -0.0879 0.5446 0.8460 6.750 1.0803 0.01500 0.00893 -0.0852 0.5248 0.8509 7.000 1.0937 0.01512 0.00902 -0.0825 0.5034 0.8567 7.250 1.1019 0.01530 0.00916 -0.0788 0.4773 0.8623 7.500 1.1060 0.01558 0.00938 -0.0744 0.4480 0.8689 7.750 1.1050 0.01620 0.00981 -0.0694 0.4072 0.8769 8.000 1.0965 0.01718 0.01052 -0.0635 0.3480 0.8866 8.250 1.0788 0.01887 0.01175 -0.0571 0.2612 0.8996 8.500 1.0585 0.02171 0.01398 -0.0521 0.1503 0.9304 8.750 1.0497 0.02379 0.01575 -0.0484 0.1087 1.0000 9.000 1.0511 0.02559 0.01745 -0.0462 0.0970 1.0000 9.250 1.0580 0.02709 0.01900 -0.0447 0.0912 1.0000 9.500 1.0614 0.02887 0.02077 -0.0429 0.0869 1.0000 9.750 1.0627 0.03086 0.02276 -0.0411 0.0838 1.0000 10.000 1.0721 0.03232 0.02430 -0.0400 0.0815 1.0000 10.250 1.0806 0.03388 0.02591 -0.0388 0.0794 1.0000 10.500 1.0897 0.03541 0.02747 -0.0377 0.0775 1.0000 10.750 1.0997 0.03691 0.02899 -0.0367 0.0758 1.0000 11.000 1.1113 0.03834 0.03041 -0.0356 0.0741 1.0000 11.250 1.1283 0.03957 0.03157 -0.0347 0.0721 1.0000 11.500 1.1509 0.04052 0.03254 -0.0341 0.0705 1.0000 11.750 1.1685 0.04158 0.03369 -0.0335 0.0692 1.0000 12.000 1.1863 0.04268 0.03487 -0.0329 0.0673 1.0000 12.250 1.2022 0.04388 0.03613 -0.0323 0.0650 1.0000 12.500 1.2171 0.04516 0.03741 -0.0318 0.0622 1.0000 12.750 1.2435 0.04642 0.03865 -0.0318 0.0586 1.0000 13.000 1.2508 0.04792 0.04031 -0.0309 0.0570 1.0000 13.250 1.2622 0.04940 0.04191 -0.0301 0.0549 1.0000 13.500 1.2730 0.05093 0.04352 -0.0295 0.0529 1.0000 13.750 1.2872 0.05238 0.04495 -0.0291 0.0506 1.0000 14.000 1.3022 0.05428 0.04698 -0.0286 0.0480 1.0000 14.250 1.3018 0.05638 0.04928 -0.0277 0.0459 1.0000 14.500 1.3039 0.05844 0.05145 -0.0270 0.0437 1.0000 14.750 1.3101 0.06028 0.05327 -0.0267 0.0417 1.0000 15.000 1.3150 0.06299 0.05616 -0.0260 0.0391 1.0000 15.250 1.3134 0.06576 0.05914 -0.0255 0.0370 1.0000 15.500 1.3142 0.06830 0.06178 -0.0253 0.0353 1.0000 15.750 1.3286 0.07037 0.06376 -0.0251 0.0332 1.0000 16.000 1.3166 0.07430 0.06804 -0.0249 0.0321 1.0000 16.250 1.3095 0.07813 0.07213 -0.0250 0.0308 1.0000 16.500 1.3066 0.08152 0.07568 -0.0253 0.0297 1.0000 16.750 1.3048 0.08464 0.07890 -0.0258 0.0288 1.0000 17.000 1.3070 0.08731 0.08158 -0.0264 0.0279 1.0000 17.250 1.3065 0.09102 0.08537 -0.0269 0.0271 1.0000 17.500 1.2901 0.09664 0.09131 -0.0283 0.0267 1.0000 17.750 1.2717 0.10285 0.09784 -0.0303 0.0264 1.0000 18.000 1.2518 0.10959 0.10486 -0.0329 0.0261 1.0000 18.250 1.2301 0.11691 0.11247 -0.0361 0.0260 1.0000 18.500 1.2073 0.12482 0.12062 -0.0401 0.0259 1.0000 18.750 1.1819 0.13361 0.12966 -0.0450 0.0260 1.0000 19.000 1.1541 0.14345 0.13972 -0.0509 0.0262 1.0000 19.250 1.1258 0.15405 0.15051 -0.0577 0.0265 1.0000