XFOIL Version 6.94 Calculated polar for: NACA M24 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 0.3429 0.01642 0.00786 -0.0269 0.5373 0.0392 0.500 0.3989 0.01631 0.00778 -0.0274 0.5287 0.0496 1.000 0.4560 0.01542 0.00660 -0.0273 0.5207 0.0512 1.500 0.5112 0.01486 0.00613 -0.0273 0.5129 0.0559 2.000 0.5648 0.01437 0.00569 -0.0269 0.5049 0.0616 2.500 0.6178 0.01421 0.00552 -0.0264 0.4969 0.0819 3.000 0.6673 0.01361 0.00560 -0.0257 0.4891 0.2926 3.500 0.8705 0.01324 0.00650 -0.0567 0.4775 1.0000 4.000 0.9233 0.01351 0.00674 -0.0566 0.4696 1.0000 4.500 0.9755 0.01366 0.00685 -0.0565 0.4609 1.0000 5.000 1.0253 0.01333 0.00633 -0.0556 0.4364 1.0000 5.500 1.0748 0.01342 0.00626 -0.0551 0.4102 1.0000 6.000 1.1240 0.01371 0.00650 -0.0546 0.3881 1.0000 6.500 1.1718 0.01415 0.00689 -0.0540 0.3664 1.0000 7.000 1.2156 0.01492 0.00748 -0.0530 0.3310 1.0000 7.500 1.2552 0.01596 0.00837 -0.0515 0.2917 1.0000 8.000 1.2601 0.01931 0.01103 -0.0462 0.1788 1.0000 8.500 1.2072 0.02390 0.01526 -0.0332 0.0982 1.0000 9.000 1.1584 0.02980 0.02096 -0.0242 0.0385 1.0000 9.500 1.1406 0.03510 0.02622 -0.0200 0.0062 1.0000 10.000 1.1462 0.03894 0.03019 -0.0178 0.0056 1.0000 10.500 1.1516 0.04312 0.03454 -0.0161 0.0053 1.0000 11.000 1.1554 0.04767 0.03926 -0.0148 0.0052 1.0000 11.500 1.1585 0.05267 0.04442 -0.0139 0.0052 1.0000 12.000 1.1606 0.05806 0.05000 -0.0134 0.0052 1.0000 12.500 1.1614 0.06380 0.05594 -0.0132 0.0052 1.0000 13.000 1.1615 0.06985 0.06217 -0.0132 0.0052 1.0000 13.500 1.1605 0.07617 0.06867 -0.0134 0.0053 1.0000 14.000 1.1588 0.08277 0.07546 -0.0139 0.0054 1.0000 14.500 1.1557 0.08966 0.08254 -0.0146 0.0055 1.0000 15.000 1.1517 0.09685 0.08990 -0.0155 0.0056 1.0000 15.500 1.1467 0.10430 0.09752 -0.0167 0.0057 1.0000 16.000 1.1422 0.11177 0.10515 -0.0181 0.0058 1.0000 16.500 1.1408 0.11879 0.11229 -0.0195 0.0060 1.0000 17.000 1.1438 0.12493 0.11852 -0.0207 0.0062 1.0000 17.500 1.1540 0.12959 0.12321 -0.0214 0.0064 1.0000 18.000 1.1757 0.13176 0.12536 -0.0208 0.0067 1.0000 18.500 1.1907 0.13632 0.13014 -0.0220 0.0071 1.0000 19.000 1.2208 0.13676 0.13073 -0.0200 0.0080 1.0000 19.500 1.2535 0.13677 0.13085 -0.0179 0.0088 1.0000 20.000 1.3027 0.13395 0.12857 -0.0099 0.0129 1.0000 21.000 0.9768 0.14002 0.13543 -0.0038 0.0088 1.0000 21.500 0.9519 0.14797 0.14393 -0.0072 0.0099 1.0000 22.000 0.9541 0.15122 0.14736 -0.0080 0.0109 1.0000 22.500 0.9007 0.16566 0.16231 -0.0159 0.0112 1.0000 23.000 0.8512 0.18075 0.17776 -0.0237 0.0113 1.0000 23.500 0.8009 0.19839 0.19566 -0.0322 0.0112 1.0000 24.000 0.7141 0.23926 0.23657 -0.0422 0.0270 1.0000 24.500 0.7204 0.24455 0.24188 -0.0442 0.0263 1.0000 25.000 0.7144 0.25436 0.25168 -0.0481 0.0246 1.0000 25.500 0.7182 0.26050 0.25784 -0.0506 0.0231 1.0000 26.000 0.7292 0.26438 0.26176 -0.0518 0.0224 1.0000 26.500 0.7216 0.27492 0.27229 -0.0562 0.0203 1.0000 27.000 0.7274 0.28006 0.27747 -0.0584 0.0192 1.0000 27.500 0.7280 0.28785 0.28527 -0.0614 0.0184 1.0000 28.000 0.7305 0.29477 0.29221 -0.0642 0.0168 1.0000 28.500 0.7362 0.29963 0.29711 -0.0664 0.0160 1.0000 29.000 0.7366 0.30769 0.30519 -0.0695 0.0154 1.0000 29.500 0.7389 0.31468 0.31220 -0.0723 0.0142 1.0000 30.000 0.7426 0.32029 0.31785 -0.0749 0.0135 1.0000 30.500 0.7495 0.32469 0.32229 -0.0766 0.0131 1.0000 31.000 0.7468 0.33390 0.33151 -0.0803 0.0127 1.0000 31.500 0.7490 0.34069 0.33833 -0.0831 0.0119 1.0000 32.000 0.7513 0.34678 0.34445 -0.0858 0.0114 1.0000 32.500 0.7538 0.35247 0.35019 -0.0884 0.0110 1.0000 33.000 0.7572 0.35736 0.35512 -0.0908 0.0107 1.0000 33.500 0.7582 0.36402 0.36181 -0.0935 0.0106 1.0000 34.000 0.7585 0.37126 0.36908 -0.0966 0.0105 1.0000 34.500 0.7594 0.37793 0.37578 -0.0994 0.0103 1.0000 35.000 0.7604 0.38417 0.38207 -0.1021 0.0100 1.0000 35.500 0.7612 0.39017 0.38811 -0.1049 0.0098 1.0000 36.000 0.7618 0.39605 0.39402 -0.1076 0.0095 1.0000 36.500 0.7623 0.40181 0.39983 -0.1103 0.0093 1.0000 37.000 0.7625 0.40748 0.40554 -0.1131 0.0091 1.0000 37.500 0.7624 0.41296 0.41107 -0.1158 0.0090 1.0000 38.000 0.7622 0.41825 0.41640 -0.1185 0.0088 1.0000 38.500 0.7617 0.42321 0.42141 -0.1211 0.0086 1.0000 39.500 0.7596 0.43516 0.43343 -0.1265 0.0084 1.0000 40.000 0.7586 0.44172 0.44003 -0.1291 0.0078 1.0000 40.500 0.7572 0.44717 0.44551 -0.1317 0.0072 1.0000 41.000 0.7555 0.45186 0.45025 -0.1344 0.0068 1.0000 42.000 0.7517 0.46431 0.46276 -0.1394 0.0063 1.0000 42.500 0.7495 0.46985 0.46834 -0.1419 0.0056 1.0000 43.000 0.7470 0.47452 0.47305 -0.1444 0.0052 1.0000 43.500 0.7439 0.47820 0.47678 -0.1470 0.0050 1.0000 44.000 0.7412 0.48513 0.48373 -0.1494 0.0049 1.0000 44.500 0.7386 0.49115 0.48977 -0.1517 0.0044 1.0000 45.000 0.7353 0.49582 0.49449 -0.1541 0.0039 1.0000 45.500 0.7316 0.49972 0.49842 -0.1567 0.0036 1.0000 46.500 0.7238 0.50934 0.50810 -0.1614 0.0034 1.0000 47.000 0.7204 0.51479 0.51358 -0.1636 0.0032 1.0000 47.500 0.7162 0.51906 0.51788 -0.1659 0.0028 1.0000 48.000 0.7117 0.52261 0.52147 -0.1682 0.0025 1.0000 48.500 0.7066 0.52540 0.52430 -0.1707 0.0023 1.0000 49.000 0.7009 0.52755 0.52649 -0.1731 0.0022 1.0000 50.000 0.6916 0.53694 0.53592 -0.1773 0.0021 1.0000 50.500 0.6866 0.54063 0.53964 -0.1794 0.0020 1.0000 51.000 0.6812 0.54375 0.54279 -0.1815 0.0018 1.0000 51.500 0.6755 0.54647 0.54554 -0.1837 0.0016 1.0000 52.000 0.6695 0.54870 0.54780 -0.1858 0.0014 1.0000 52.500 0.6632 0.55039 0.54952 -0.1880 0.0012 1.0000 53.000 0.6565 0.55162 0.55079 -0.1902 0.0011 1.0000 53.500 0.6492 0.55220 0.55139 -0.1925 0.0010 1.0000 54.500 0.6370 0.55735 0.55659 -0.1962 0.0009 1.0000 55.000 0.6302 0.55859 0.55786 -0.1981 0.0008 1.0000 55.500 0.6231 0.55932 0.55862 -0.2001 0.0007 1.0000 56.000 0.6157 0.55960 0.55893 -0.2021 0.0006 1.0000 56.500 0.6079 0.55935 0.55871 -0.2042 0.0005 1.0000 58.000 0.5853 0.55997 0.55940 -0.2095 0.0004 1.0000 58.500 0.5774 0.55936 0.55882 -0.2113 0.0004 1.0000 59.000 0.5693 0.55838 0.55786 -0.2131 0.0003 1.0000 59.500 0.5610 0.55717 0.55668 -0.2149 0.0001 1.0000 60.000 0.5525 0.55540 0.55494 -0.2166 0.0000 1.0000