XFOIL Version 6.94 Calculated polar for: EPPLER 542 AIRFOIL 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 0.2379 0.01504 0.00970 -0.0316 0.6637 0.8099 0.500 0.2902 0.01488 0.00956 -0.0312 0.6566 0.8115 1.000 0.3435 0.01480 0.00945 -0.0311 0.6490 0.8136 1.500 0.3931 0.01467 0.00925 -0.0306 0.6413 0.8160 2.000 0.4352 0.01437 0.00899 -0.0287 0.6329 0.8198 2.500 0.4797 0.01396 0.00854 -0.0277 0.6242 0.8229 3.000 0.5270 0.01370 0.00827 -0.0274 0.6156 0.8263 3.500 0.5770 0.01340 0.00799 -0.0274 0.6058 0.8281 4.000 0.6268 0.01313 0.00773 -0.0269 0.5961 0.8295 4.500 0.6741 0.01290 0.00758 -0.0258 0.5850 0.8310 5.500 0.7701 0.01268 0.00747 -0.0239 0.5598 0.8342 6.000 0.8155 0.01257 0.00747 -0.0226 0.5446 0.8358 6.500 0.8588 0.01248 0.00745 -0.0208 0.5257 0.8375 7.000 0.8980 0.01244 0.00747 -0.0182 0.5017 0.8393 7.500 0.9266 0.01251 0.00751 -0.0136 0.4695 0.8415 8.000 0.9438 0.01283 0.00775 -0.0069 0.4255 0.8445 8.500 0.9529 0.01371 0.00845 0.0007 0.3692 0.8466 9.000 0.9536 0.01495 0.00946 0.0090 0.3143 0.8487 9.500 0.9529 0.01640 0.01074 0.0169 0.2638 0.8514 10.000 0.9547 0.01815 0.01236 0.0235 0.2216 0.8539 10.500 0.9580 0.02017 0.01427 0.0292 0.1836 0.8566 11.000 0.9623 0.02243 0.01645 0.0340 0.1501 0.8594 11.500 0.9676 0.02490 0.01884 0.0382 0.1208 0.8627 12.000 0.9734 0.02761 0.02146 0.0417 0.0950 0.8652 12.500 0.9788 0.03058 0.02437 0.0447 0.0733 0.8673 13.000 0.9847 0.03365 0.02742 0.0472 0.0554 0.8701 13.500 0.9900 0.03697 0.03078 0.0495 0.0429 0.8731 14.000 0.9940 0.04070 0.03455 0.0512 0.0346 0.8762 14.500 1.0018 0.04438 0.03835 0.0523 0.0281 0.8794 15.000 1.0067 0.04860 0.04267 0.0530 0.0235 0.8827 15.500 1.0100 0.05328 0.04745 0.0531 0.0194 0.8859 16.000 1.0104 0.05856 0.05288 0.0528 0.0164 0.8893 16.500 1.0139 0.06369 0.05821 0.0520 0.0132 0.8939 17.000 1.0090 0.07014 0.06485 0.0507 0.0113 0.8989 17.500 1.0063 0.07685 0.07180 0.0487 0.0094 0.9040 18.500 0.9877 0.09332 0.08876 0.0422 0.0074 0.9162 19.000 0.9745 0.10295 0.09859 0.0375 0.0068 0.9248 19.500 0.9663 0.11286 0.10882 0.0317 0.0063 0.9398 20.000 0.9648 0.12312 0.11939 0.0236 0.0060 0.9926