XFOIL Version 6.96 Calculated polar for: EPPLER E854 AIRFOIL 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 -0.5365 0.06377 0.06217 -0.0569 1.0000 0.0068 -9.750 -0.6095 0.02614 0.02271 -0.0978 0.9832 0.0052 -9.500 -0.5948 0.02392 0.02024 -0.0976 0.9765 0.0051 -9.250 -0.5680 0.02181 0.01789 -0.0996 0.9738 0.0051 -9.000 -0.5379 0.02004 0.01592 -0.1017 0.9720 0.0051 -8.750 -0.5187 0.01846 0.01417 -0.1011 0.9654 0.0052 -8.500 -0.4910 0.01691 0.01247 -0.1023 0.9615 0.0053 -8.250 -0.4595 0.01581 0.01127 -0.1039 0.9591 0.0055 -8.000 -0.4397 0.01487 0.01024 -0.1028 0.9498 0.0056 -7.750 -0.4087 0.01392 0.00920 -0.1041 0.9458 0.0057 -7.500 -0.3815 0.01298 0.00815 -0.1045 0.9370 0.0058 -7.250 -0.3430 0.01204 0.00710 -0.1073 0.9326 0.0058 -7.000 -0.3032 0.01123 0.00618 -0.1104 0.9248 0.0060 -6.750 -0.2552 0.01051 0.00535 -0.1152 0.9175 0.0063 -6.500 -0.2133 0.00996 0.00467 -0.1185 0.9031 0.0067 -6.250 -0.1797 0.00951 0.00407 -0.1200 0.8835 0.0077 -6.000 -0.1515 0.00910 0.00353 -0.1203 0.8626 0.0118 -5.750 -0.1259 0.00876 0.00317 -0.1200 0.8429 0.0237 -5.500 -0.1004 0.00856 0.00293 -0.1197 0.8245 0.0339 -5.250 -0.0750 0.00839 0.00272 -0.1194 0.8080 0.0457 -5.000 -0.0495 0.00822 0.00253 -0.1190 0.7924 0.0610 -4.750 -0.0242 0.00797 0.00233 -0.1187 0.7777 0.0912 -4.500 0.0010 0.00763 0.00212 -0.1185 0.7641 0.1373 -4.250 0.0264 0.00725 0.00190 -0.1184 0.7515 0.2010 -4.000 0.0515 0.00677 0.00168 -0.1183 0.7393 0.2926 -3.750 0.0774 0.00648 0.00156 -0.1182 0.7279 0.3656 -3.500 0.1041 0.00640 0.00151 -0.1180 0.7169 0.4012 -3.250 0.1314 0.00636 0.00147 -0.1180 0.7065 0.4270 -3.000 0.1588 0.00637 0.00144 -0.1179 0.6968 0.4444 -2.750 0.1861 0.00639 0.00141 -0.1178 0.6874 0.4560 -2.500 0.2138 0.00640 0.00139 -0.1178 0.6781 0.4679 -2.250 0.2415 0.00644 0.00137 -0.1177 0.6698 0.4765 -2.000 0.2689 0.00646 0.00136 -0.1177 0.6615 0.4851 -1.750 0.2968 0.00649 0.00135 -0.1177 0.6537 0.4932 -1.250 0.3521 0.00655 0.00137 -0.1176 0.6388 0.5129 -1.000 0.3797 0.00662 0.00138 -0.1176 0.6319 0.5206 -0.750 0.4076 0.00661 0.00139 -0.1176 0.6254 0.5268 -0.500 0.4352 0.00666 0.00140 -0.1176 0.6187 0.5323 -0.250 0.4631 0.00669 0.00141 -0.1177 0.6127 0.5374 0.000 0.4909 0.00672 0.00144 -0.1177 0.6067 0.5428 0.250 0.5184 0.00678 0.00146 -0.1177 0.6011 0.5483 0.500 0.5464 0.00679 0.00149 -0.1177 0.5954 0.5537 0.750 0.5739 0.00684 0.00153 -0.1177 0.5899 0.5595 1.000 0.6017 0.00689 0.00157 -0.1177 0.5850 0.5654 1.250 0.6295 0.00691 0.00162 -0.1178 0.5796 0.5716 1.500 0.6568 0.00699 0.00168 -0.1177 0.5745 0.5782 1.750 0.6847 0.00701 0.00174 -0.1178 0.5698 0.5849 2.000 0.7123 0.00705 0.00180 -0.1178 0.5647 0.5924 2.250 0.7394 0.00713 0.00188 -0.1177 0.5595 0.5998 2.500 0.7672 0.00716 0.00195 -0.1177 0.5538 0.6084 2.750 0.7941 0.00721 0.00202 -0.1176 0.5471 0.6172 3.000 0.8213 0.00726 0.00211 -0.1175 0.5404 0.6266 3.250 0.8480 0.00732 0.00219 -0.1174 0.5326 0.6373 3.500 0.8750 0.00737 0.00228 -0.1172 0.5245 0.6488 3.750 0.9010 0.00746 0.00237 -0.1169 0.5155 0.6611 4.000 0.9281 0.00749 0.00248 -0.1168 0.5068 0.6745 4.250 0.9544 0.00757 0.00259 -0.1166 0.4993 0.6897 4.500 0.9808 0.00763 0.00271 -0.1164 0.4903 0.7066 4.750 1.0071 0.00770 0.00285 -0.1162 0.4817 0.7252 5.000 1.0325 0.00779 0.00299 -0.1158 0.4711 0.7457 5.250 1.0579 0.00788 0.00314 -0.1153 0.4597 0.7700 5.500 1.0820 0.00799 0.00331 -0.1147 0.4432 0.7994 5.750 1.1051 0.00811 0.00349 -0.1138 0.4234 0.8366 6.000 1.1237 0.00825 0.00372 -0.1119 0.3991 0.8953 6.250 1.1437 0.00854 0.00396 -0.1104 0.3608 1.0000 6.500 1.1606 0.00924 0.00437 -0.1086 0.3048 1.0000 6.750 1.1738 0.01016 0.00495 -0.1062 0.2399 1.0000 7.000 1.1876 0.01101 0.00551 -0.1039 0.1874 1.0000 7.250 1.2030 0.01172 0.00602 -0.1018 0.1499 1.0000 7.500 1.2179 0.01240 0.00653 -0.0997 0.1171 1.0000 7.750 1.2316 0.01304 0.00702 -0.0973 0.0916 1.0000 8.000 1.2440 0.01367 0.00752 -0.0947 0.0711 1.0000 8.250 1.2578 0.01422 0.00800 -0.0923 0.0565 1.0000 8.500 1.2719 0.01478 0.00850 -0.0900 0.0450 1.0000 8.750 1.2852 0.01536 0.00903 -0.0877 0.0351 1.0000 9.000 1.2989 0.01594 0.00958 -0.0855 0.0285 1.0000 9.250 1.3135 0.01648 0.01013 -0.0834 0.0238 1.0000 9.500 1.3259 0.01712 0.01076 -0.0811 0.0191 1.0000 9.750 1.3394 0.01772 0.01138 -0.0790 0.0163 1.0000 10.000 1.3511 0.01843 0.01209 -0.0767 0.0130 1.0000 10.250 1.3613 0.01922 0.01288 -0.0743 0.0101 1.0000 10.500 1.3719 0.02002 0.01372 -0.0721 0.0080 1.0000 10.750 1.3791 0.02106 0.01477 -0.0695 0.0060 1.0000 11.000 1.3872 0.02209 0.01584 -0.0671 0.0047 1.0000 11.250 1.3929 0.02333 0.01716 -0.0647 0.0036 1.0000 11.500 1.4010 0.02447 0.01837 -0.0627 0.0033 1.0000 11.750 1.4076 0.02578 0.01974 -0.0607 0.0029 1.0000 12.000 1.4074 0.02767 0.02174 -0.0582 0.0025 1.0000 12.250 1.4148 0.02907 0.02321 -0.0566 0.0023 1.0000 12.500 1.4202 0.03070 0.02492 -0.0551 0.0022 1.0000 12.750 1.4254 0.03240 0.02671 -0.0537 0.0022 1.0000 13.000 1.4304 0.03420 0.02858 -0.0524 0.0020 1.0000 13.250 1.4341 0.03619 0.03066 -0.0512 0.0019 1.0000 13.500 1.4372 0.03829 0.03285 -0.0502 0.0018 1.0000 13.750 1.4391 0.04060 0.03525 -0.0493 0.0017 1.0000 14.000 1.4406 0.04305 0.03779 -0.0485 0.0017 1.0000 14.250 1.4415 0.04564 0.04049 -0.0479 0.0017 1.0000 14.500 1.4393 0.04865 0.04360 -0.0474 0.0016 1.0000 14.750 1.4383 0.05166 0.04672 -0.0471 0.0016 1.0000 15.000 1.4328 0.05531 0.05049 -0.0470 0.0015 1.0000 15.250 1.4297 0.05879 0.05408 -0.0471 0.0015 1.0000 15.500 1.4167 0.06373 0.05918 -0.0476 0.0014 1.0000 15.750 1.4160 0.06718 0.06273 -0.0481 0.0015 1.0000 16.000 1.4063 0.07199 0.06769 -0.0490 0.0014 1.0000 16.250 1.3966 0.07700 0.07284 -0.0501 0.0014 1.0000 16.500 1.3903 0.08166 0.07762 -0.0514 0.0014 1.0000 16.750 1.3807 0.08700 0.08310 -0.0531 0.0014 1.0000 17.000 1.3692 0.09280 0.08905 -0.0551 0.0014 1.0000 17.250 1.3594 0.09852 0.09490 -0.0573 0.0014 1.0000 17.500 1.3499 0.10434 0.10086 -0.0597 0.0014 1.0000