XFOIL Version 6.94 Calculated polar for: NACA 63(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 0.4988 0.00992 0.00408 -0.1100 0.6115 0.5941 0.500 0.5573 0.01027 0.00438 -0.1108 0.6000 0.5990 1.000 0.6143 0.01010 0.00431 -0.1113 0.5953 0.6156 1.500 0.6709 0.01014 0.00445 -0.1115 0.5879 0.6261 2.000 0.7275 0.01026 0.00458 -0.1118 0.5799 0.6361 2.500 0.7834 0.01042 0.00468 -0.1120 0.5694 0.6444 3.000 0.8399 0.01082 0.00499 -0.1124 0.5535 0.6522 3.500 0.8949 0.01094 0.00525 -0.1126 0.5481 0.6678 4.000 0.9485 0.01103 0.00547 -0.1123 0.5426 0.6796 4.500 1.0017 0.01116 0.00566 -0.1120 0.5337 0.6904 5.000 1.0516 0.01127 0.00568 -0.1109 0.5165 0.6981 5.500 1.0977 0.01135 0.00579 -0.1092 0.4942 0.7170 6.000 1.1397 0.01148 0.00609 -0.1067 0.4719 0.7304 6.500 1.1751 0.01191 0.00647 -0.1031 0.4473 0.7423 7.000 1.2108 0.01216 0.00681 -0.0996 0.4292 0.7541 7.500 1.2177 0.01265 0.00731 -0.0907 0.4037 0.7736 8.000 1.2431 0.01322 0.00795 -0.0857 0.3818 0.7901 8.500 1.2369 0.01444 0.00908 -0.0759 0.3445 0.8105 9.000 1.2234 0.01611 0.01067 -0.0658 0.3037 0.8363 9.500 1.2150 0.01795 0.01254 -0.0574 0.2684 0.8660 10.000 1.1897 0.02011 0.01478 -0.0468 0.2376 0.9351 10.500 1.1840 0.02329 0.01779 -0.0420 0.1983 1.0000 11.000 1.1881 0.02618 0.02059 -0.0382 0.1703 1.0000 11.500 1.1847 0.02973 0.02406 -0.0344 0.1418 1.0000 12.000 1.1888 0.03310 0.02741 -0.0316 0.1241 1.0000 12.500 1.1868 0.03717 0.03138 -0.0288 0.0990 1.0000 13.000 1.1853 0.04150 0.03571 -0.0267 0.0816 1.0000 13.500 1.1824 0.04619 0.04029 -0.0250 0.0656 1.0000 14.000 1.1784 0.05133 0.04539 -0.0239 0.0524 1.0000 14.500 1.1836 0.05589 0.05001 -0.0234 0.0410 1.0000 15.000 1.1864 0.06096 0.05506 -0.0231 0.0315 1.0000 15.500 1.1653 0.06920 0.06360 -0.0233 0.0201 1.0000 16.000 1.1786 0.07364 0.06816 -0.0239 0.0195 1.0000 16.500 1.1793 0.07987 0.07457 -0.0252 0.0186 1.0000 17.000 1.1868 0.08535 0.08020 -0.0264 0.0177 1.0000 17.500 1.1952 0.09085 0.08585 -0.0278 0.0167 1.0000 18.000 1.1944 0.09794 0.09311 -0.0302 0.0158 1.0000 18.500 1.2001 0.10417 0.09947 -0.0324 0.0150 1.0000 19.000 1.2075 0.11010 0.10555 -0.0346 0.0142 1.0000 19.500 1.2087 0.11707 0.11267 -0.0376 0.0136 1.0000 20.000 1.2045 0.12507 0.12086 -0.0413 0.0132 1.0000 20.500 1.2058 0.13201 0.12798 -0.0446 0.0129 1.0000 21.000 1.1953 0.14114 0.13735 -0.0492 0.0128 1.0000 21.500 1.1878 0.14975 0.14618 -0.0538 0.0126 1.0000 22.000 1.1759 0.15905 0.15571 -0.0589 0.0125 1.0000 22.500 1.1483 0.17166 0.16862 -0.0662 0.0125 1.0000 23.000 1.0963 0.18973 0.18707 -0.0766 0.0127 1.0000 23.500 0.9319 0.23886 0.23652 -0.0986 0.0142 1.0000 24.000 0.9257 0.25008 0.24772 -0.1031 0.0145 1.0000 24.500 0.9264 0.25901 0.25663 -0.1070 0.0146 1.0000 25.000 0.9300 0.26691 0.26453 -0.1105 0.0145 1.0000 25.500 0.9348 0.27425 0.27186 -0.1139 0.0142 1.0000 26.000 0.9408 0.28098 0.27858 -0.1171 0.0136 1.0000 26.500 0.9484 0.28676 0.28436 -0.1203 0.0125 1.0000 27.000 0.9593 0.29069 0.28828 -0.1231 0.0112 1.0000 27.500 0.9713 0.29372 0.29131 -0.1258 0.0103 1.0000 28.000 0.9817 0.29690 0.29449 -0.1286 0.0094 1.0000 28.500 0.9791 0.30760 0.30516 -0.1325 0.0065 1.0000