XFOIL Version 6.96 Calculated polar for: NACA 65(3)-218 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -0.9256 0.11123 0.10758 -0.0428 1.0000 0.0155 -19.500 -0.9432 0.10406 0.10027 -0.0469 1.0000 0.0156 -19.250 -0.9555 0.09806 0.09413 -0.0502 1.0000 0.0157 -19.000 -0.9657 0.09260 0.08855 -0.0531 1.0000 0.0158 -18.750 -0.9726 0.08784 0.08370 -0.0555 1.0000 0.0159 -18.500 -0.9797 0.08317 0.07892 -0.0578 1.0000 0.0160 -18.250 -0.9841 0.07903 0.07468 -0.0597 1.0000 0.0161 -18.000 -0.9861 0.07535 0.07092 -0.0613 1.0000 0.0162 -17.750 -0.9879 0.07182 0.06731 -0.0628 1.0000 0.0163 -17.500 -0.9895 0.06840 0.06378 -0.0641 1.0000 0.0164 -17.250 -0.9891 0.06532 0.06062 -0.0652 1.0000 0.0166 -17.000 -0.9896 0.06226 0.05745 -0.0660 1.0000 0.0167 -16.750 -0.9881 0.05950 0.05460 -0.0667 1.0000 0.0168 -16.500 -0.9859 0.05690 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0.6641 3.250 0.5408 0.00894 0.00310 -0.0425 0.5977 0.6672 3.500 0.5688 0.00898 0.00316 -0.0427 0.5923 0.6705 3.750 0.5965 0.00902 0.00323 -0.0428 0.5858 0.6738 4.000 0.6234 0.00905 0.00326 -0.0428 0.5746 0.6771 4.250 0.6498 0.00909 0.00331 -0.0427 0.5604 0.6801 4.500 0.6757 0.00914 0.00338 -0.0424 0.5449 0.6832 4.750 0.6998 0.00927 0.00346 -0.0419 0.5215 0.6868 5.000 0.7219 0.00949 0.00360 -0.0410 0.4872 0.6908 5.250 0.7357 0.01008 0.00389 -0.0388 0.4216 0.6949 5.500 0.7419 0.01103 0.00446 -0.0354 0.3445 0.6986 5.750 0.7489 0.01187 0.00504 -0.0322 0.2831 0.7025 6.000 0.7538 0.01270 0.00562 -0.0287 0.2273 0.7068 6.250 0.7562 0.01339 0.00613 -0.0246 0.1866 0.7113 6.500 0.7605 0.01416 0.00674 -0.0211 0.1508 0.7156 6.750 0.7665 0.01493 0.00740 -0.0181 0.1203 0.7201 7.000 0.7727 0.01577 0.00813 -0.0153 0.0919 0.7254 7.250 0.7810 0.01660 0.00886 -0.0129 0.0707 0.7307 7.500 0.7894 0.01745 0.00964 -0.0107 0.0520 0.7357 7.750 0.8010 0.01819 0.01036 -0.0089 0.0427 0.7410 8.000 0.8139 0.01891 0.01109 -0.0074 0.0369 0.7465 8.250 0.8273 0.01963 0.01182 -0.0060 0.0338 0.7516 8.500 0.8414 0.02031 0.01255 -0.0047 0.0314 0.7571 8.750 0.8543 0.02109 0.01336 -0.0034 0.0295 0.7632 9.000 0.8685 0.02183 0.01415 -0.0023 0.0281 0.7692 9.250 0.8821 0.02259 0.01498 -0.0011 0.0266 0.7758 9.500 0.8953 0.02342 0.01585 0.0001 0.0256 0.7828 9.750 0.9066 0.02437 0.01684 0.0014 0.0244 0.7894 10.000 0.9202 0.02519 0.01773 0.0024 0.0235 0.7967 10.500 0.9455 0.02700 0.01969 0.0045 0.0220 0.8114 10.750 0.9576 0.02799 0.02073 0.0056 0.0215 0.8195 11.000 0.9684 0.02904 0.02185 0.0067 0.0211 0.8282 11.250 0.9770 0.03029 0.02315 0.0079 0.0203 0.8380 11.500 0.9879 0.03133 0.02429 0.0089 0.0200 0.8481 11.750 0.9987 0.03243 0.02548 0.0099 0.0197 0.8591 12.000 1.0088 0.03359 0.02674 0.0109 0.0192 0.8716 12.250 1.0179 0.03480 0.02805 0.0120 0.0189 0.8862 12.500 1.0270 0.03601 0.02937 0.0131 0.0186 0.9057 12.750 1.0386 0.03731 0.03079 0.0135 0.0182 0.9339 13.000 1.0606 0.03892 0.03249 0.0111 0.0178 0.9941 13.250 1.0674 0.04034 0.03394 0.0123 0.0175 1.0000 13.500 1.0765 0.04196 0.03559 0.0126 0.0172 1.0000 13.750 1.0835 0.04378 0.03745 0.0130 0.0169 1.0000 14.000 1.0933 0.04541 0.03913 0.0132 0.0166 1.0000 14.250 1.1024 0.04711 0.04090 0.0134 0.0163 1.0000 14.500 1.1112 0.04886 0.04272 0.0136 0.0162 1.0000 14.750 1.1193 0.05074 0.04466 0.0137 0.0159 1.0000 15.000 1.1269 0.05268 0.04666 0.0138 0.0156 1.0000 15.250 1.1346 0.05465 0.04871 0.0138 0.0155 1.0000 15.500 1.1413 0.05676 0.05088 0.0138 0.0154 1.0000 15.750 1.1481 0.05889 0.05308 0.0136 0.0151 1.0000 16.000 1.1548 0.06108 0.05534 0.0134 0.0149 1.0000 16.250 1.1605 0.06343 0.05775 0.0131 0.0148 1.0000 16.500 1.1658 0.06585 0.06024 0.0128 0.0147 1.0000 16.750 1.1706 0.06840 0.06285 0.0123 0.0145 1.0000 17.000 1.1749 0.07101 0.06555 0.0118 0.0144 1.0000 17.250 1.1787 0.07375 0.06837 0.0112 0.0144 1.0000 17.500 1.1815 0.07670 0.07137 0.0104 0.0142 1.0000 17.750 1.1838 0.07973 0.07448 0.0096 0.0140 1.0000 18.000 1.1854 0.08291 0.07772 0.0086 0.0139 1.0000 18.250 1.1861 0.08622 0.08112 0.0076 0.0138 1.0000 18.500 1.1863 0.08968 0.08466 0.0065 0.0137 1.0000 18.750 1.1863 0.09331 0.08841 0.0051 0.0137 1.0000 19.000 1.1858 0.09709 0.09231 0.0036 0.0136 1.0000 19.250 1.1845 0.10101 0.09636 0.0019 0.0135 1.0000