XFOIL Version 6.94 Calculated polar for: NACA M18 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.2440 0.01275 0.00410 -0.0290 0.6002 0.0635 0.500 0.2957 0.01205 0.00375 -0.0281 0.5861 0.1573 1.500 0.5311 0.01092 0.00465 -0.0532 0.5546 1.0000 2.000 0.5837 0.01100 0.00460 -0.0528 0.5422 1.0000 2.500 0.6362 0.01111 0.00460 -0.0524 0.5306 1.0000 3.000 0.6886 0.01124 0.00465 -0.0520 0.5193 1.0000 3.500 0.7403 0.01137 0.00470 -0.0515 0.5067 1.0000 4.000 0.7918 0.01156 0.00484 -0.0509 0.4956 1.0000 4.500 0.8425 0.01179 0.00505 -0.0501 0.4848 1.0000 5.000 0.8908 0.01190 0.00509 -0.0489 0.4626 1.0000 5.500 0.9402 0.01217 0.00540 -0.0480 0.4506 1.0000 6.000 0.9870 0.01237 0.00560 -0.0465 0.4259 1.0000 6.500 1.0332 0.01266 0.00588 -0.0450 0.4008 1.0000 7.000 1.0781 0.01304 0.00627 -0.0434 0.3721 1.0000 7.500 1.1216 0.01352 0.00672 -0.0415 0.3371 1.0000 8.000 1.1514 0.01493 0.00764 -0.0379 0.2482 1.0000 8.500 1.1741 0.01674 0.00907 -0.0333 0.1775 1.0000 9.000 1.1777 0.01933 0.01116 -0.0260 0.0960 1.0000 9.500 1.1595 0.02219 0.01371 -0.0157 0.0365 1.0000 10.000 1.1705 0.02435 0.01591 -0.0111 0.0262 1.0000 10.500 1.1850 0.02699 0.01863 -0.0082 0.0139 1.0000 11.000 1.1938 0.03061 0.02230 -0.0060 0.0087 1.0000 11.500 1.2059 0.03429 0.02615 -0.0046 0.0078 1.0000 12.000 1.2160 0.03839 0.03044 -0.0035 0.0074 1.0000 12.500 1.2225 0.04302 0.03533 -0.0027 0.0071 1.0000 13.000 1.2252 0.04815 0.04069 -0.0022 0.0069 1.0000 13.500 1.2235 0.05396 0.04673 -0.0020 0.0067 1.0000 14.000 1.2185 0.06053 0.05355 -0.0022 0.0065 1.0000 14.500 1.2102 0.06784 0.06111 -0.0030 0.0062 1.0000 15.000 1.1990 0.07581 0.06932 -0.0042 0.0061 1.0000 15.500 1.1927 0.08330 0.07701 -0.0055 0.0060 1.0000 16.000 1.1858 0.09104 0.08495 -0.0071 0.0059 1.0000 16.500 1.1792 0.09883 0.09295 -0.0088 0.0059 1.0000 17.000 1.1737 0.10652 0.10087 -0.0106 0.0059 1.0000 17.500 1.1702 0.11399 0.10853 -0.0126 0.0059 1.0000 18.000 1.1676 0.12139 0.11614 -0.0147 0.0059 1.0000 18.500 1.1649 0.12896 0.12393 -0.0172 0.0060 1.0000 19.000 1.1598 0.13720 0.13243 -0.0205 0.0060 1.0000 19.500 1.1514 0.14646 0.14195 -0.0248 0.0061 1.0000 20.000 1.1433 0.15639 0.15216 -0.0302 0.0061 1.0000 20.500 1.1360 0.16668 0.16269 -0.0365 0.0062 1.0000 21.000 1.1266 0.17802 0.17428 -0.0438 0.0063 1.0000 21.500 1.1153 0.19054 0.18704 -0.0521 0.0064 1.0000 22.000 1.0986 0.20575 0.20252 -0.0623 0.0066 1.0000 22.500 1.0247 0.25095 0.24786 -0.0847 0.0102 1.0000