XFOIL Version 6.94 Calculated polar for: NACA 64(3)-618 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 0.4931 0.01030 0.00436 -0.1099 0.6085 0.5990 0.500 0.5512 0.01034 0.00441 -0.1110 0.6000 0.6108 1.000 0.6079 0.01035 0.00450 -0.1114 0.5971 0.6196 1.500 0.6642 0.01045 0.00470 -0.1118 0.5929 0.6276 2.000 0.7202 0.01057 0.00485 -0.1122 0.5871 0.6357 2.500 0.7761 0.01069 0.00498 -0.1125 0.5803 0.6432 3.000 0.8315 0.01086 0.00512 -0.1127 0.5727 0.6483 3.500 0.8862 0.01101 0.00532 -0.1129 0.5652 0.6636 4.000 0.9414 0.01158 0.00596 -0.1133 0.5537 0.6757 4.500 0.9945 0.01182 0.00632 -0.1131 0.5484 0.6870 5.000 1.0454 0.01175 0.00633 -0.1123 0.5422 0.6961 5.500 1.0914 0.01142 0.00601 -0.1104 0.5247 0.7113 6.500 1.1698 0.01165 0.00648 -0.1042 0.4854 0.7405 7.000 1.1961 0.01187 0.00673 -0.0988 0.4672 0.7528 7.500 1.2110 0.01225 0.00719 -0.0913 0.4462 0.7742 8.000 1.2314 0.01276 0.00776 -0.0853 0.4138 0.7915 8.500 1.2048 0.01429 0.00908 -0.0720 0.3596 0.8145 9.000 1.1797 0.01632 0.01100 -0.0603 0.3086 0.8419 9.500 1.1506 0.01880 0.01344 -0.0490 0.2626 0.8818 10.000 1.1265 0.02142 0.01605 -0.0396 0.2226 1.0000 10.500 1.1145 0.02509 0.01958 -0.0342 0.1793 1.0000 11.000 1.1016 0.02909 0.02340 -0.0294 0.1390 1.0000 11.500 1.0959 0.03304 0.02722 -0.0257 0.1121 1.0000 12.000 1.1001 0.03660 0.03073 -0.0232 0.0856 1.0000 12.500 1.0924 0.04130 0.03528 -0.0205 0.0656 1.0000 13.000 1.0920 0.04566 0.03952 -0.0186 0.0424 1.0000 14.000 1.0862 0.05587 0.04986 -0.0158 0.0187 1.0000 14.500 1.0959 0.06015 0.05429 -0.0153 0.0175 1.0000 15.000 1.0979 0.06555 0.05988 -0.0152 0.0168 1.0000 15.500 1.1046 0.07050 0.06501 -0.0152 0.0163 1.0000 16.000 1.1146 0.07520 0.06990 -0.0154 0.0159 1.0000 16.500 1.1252 0.07996 0.07491 -0.0159 0.0156 1.0000 17.000 1.1321 0.08546 0.08065 -0.0166 0.0154 1.0000 17.500 1.1358 0.09167 0.08712 -0.0178 0.0153 1.0000 18.000 1.1400 0.09802 0.09375 -0.0193 0.0153 1.0000 18.500 1.1373 0.10564 0.10169 -0.0217 0.0154 1.0000 19.000 1.1175 0.11619 0.11259 -0.0260 0.0155 1.0000 19.500 1.0923 0.12808 0.12482 -0.0315 0.0157 1.0000 20.000 1.0513 0.14347 0.14058 -0.0396 0.0159 1.0000 20.500 0.9765 0.16745 0.16496 -0.0531 0.0164 1.0000 21.000 0.8538 0.20899 0.20659 -0.0721 0.0182 1.0000 21.500 0.8469 0.21935 0.21693 -0.0767 0.0185 1.0000 22.000 0.8501 0.22698 0.22454 -0.0803 0.0183 1.0000 22.500 0.8550 0.23419 0.23174 -0.0837 0.0180 1.0000 23.000 0.8574 0.24234 0.23988 -0.0873 0.0185 1.0000