XFOIL Version 6.94 Calculated polar for: EPPLER 544 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 0.2763 0.01198 0.00635 -0.0539 0.6639 0.7267 0.500 0.3318 0.01192 0.00623 -0.0547 0.6568 0.7296 1.000 0.3868 0.01170 0.00598 -0.0552 0.6494 0.7316 1.500 0.4432 0.01162 0.00585 -0.0559 0.6418 0.7334 2.000 0.4970 0.01155 0.00583 -0.0561 0.6336 0.7353 2.500 0.5517 0.01152 0.00580 -0.0563 0.6251 0.7377 3.000 0.6076 0.01159 0.00586 -0.0569 0.6165 0.7400 3.500 0.6604 0.01151 0.00585 -0.0568 0.6068 0.7424 4.500 0.7672 0.01150 0.00591 -0.0570 0.5860 0.7471 5.000 0.8209 0.01156 0.00596 -0.0571 0.5738 0.7493 5.500 0.8695 0.01149 0.00601 -0.0562 0.5601 0.7514 6.000 0.9166 0.01146 0.00609 -0.0549 0.5443 0.7544 6.500 0.9609 0.01151 0.00622 -0.0530 0.5245 0.7571 7.000 1.0011 0.01162 0.00642 -0.0503 0.4993 0.7598 7.500 1.0313 0.01189 0.00666 -0.0458 0.4639 0.7630 8.000 1.0439 0.01244 0.00707 -0.0379 0.4142 0.7664 8.500 1.0466 0.01361 0.00800 -0.0290 0.3592 0.7698 9.000 1.0498 0.01494 0.00917 -0.0209 0.3079 0.7733 9.500 1.0496 0.01663 0.01071 -0.0131 0.2606 0.7777 10.000 1.0515 0.01859 0.01256 -0.0065 0.2196 0.7824 10.500 1.0551 0.02083 0.01469 -0.0010 0.1827 0.7869 11.000 1.0592 0.02335 0.01710 0.0038 0.1496 0.7910 11.500 1.0639 0.02600 0.01970 0.0079 0.1206 0.7961 12.000 1.0688 0.02891 0.02257 0.0116 0.0955 0.8015 12.500 1.0747 0.03204 0.02567 0.0145 0.0749 0.8074 13.000 1.0811 0.03539 0.02900 0.0169 0.0585 0.8135 13.500 1.0872 0.03890 0.03258 0.0191 0.0461 0.8210 14.000 1.0943 0.04264 0.03640 0.0206 0.0368 0.8299 14.500 1.0981 0.04680 0.04069 0.0219 0.0301 0.8408 15.000 1.1054 0.05094 0.04501 0.0226 0.0247 0.8551 15.500 1.1072 0.05557 0.04989 0.0234 0.0205 0.8819 16.000 1.1175 0.06155 0.05617 0.0201 0.0165 1.0000 16.500 1.1176 0.06776 0.06252 0.0188 0.0139 1.0000 18.000 1.1005 0.09051 0.08577 0.0116 0.0090 1.0000 18.500 1.0896 0.09960 0.09510 0.0078 0.0080 1.0000 19.000 1.0802 0.10880 0.10450 0.0036 0.0073 1.0000 19.500 1.0674 0.11878 0.11465 -0.0014 0.0069 1.0000 20.000 1.0550 0.12873 0.12477 -0.0066 0.0065 1.0000 20.500 1.0477 0.13801 0.13426 -0.0117 0.0063 1.0000 21.000 1.0388 0.14768 0.14414 -0.0174 0.0059 1.0000 21.500 1.0296 0.15752 0.15417 -0.0234 0.0056 1.0000 22.000 1.0223 0.16696 0.16379 -0.0292 0.0055 1.0000 22.500 1.0134 0.17684 0.17383 -0.0355 0.0053 1.0000 23.000 1.0033 0.18710 0.18427 -0.0421 0.0052 1.0000 23.500 0.9885 0.19871 0.19607 -0.0494 0.0051 1.0000