XFOIL Version 6.94 Calculated polar for: NACA6409 9% 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 0.6782 0.00978 0.00310 -0.1491 0.7456 0.2954 0.500 0.7361 0.00833 0.00314 -0.1496 0.7208 1.0000 1.000 0.7883 0.00860 0.00309 -0.1485 0.6966 1.0000 1.500 0.8386 0.00888 0.00318 -0.1472 0.6710 1.0000 2.000 0.8895 0.00923 0.00331 -0.1460 0.6478 1.0000 2.500 0.9402 0.00960 0.00353 -0.1449 0.6266 1.0000 3.000 0.9907 0.00999 0.00381 -0.1438 0.6070 1.0000 3.500 1.0415 0.01040 0.00416 -0.1428 0.5897 1.0000 4.000 1.0925 0.01084 0.00454 -0.1419 0.5739 1.0000 4.500 1.1437 0.01132 0.00499 -0.1411 0.5593 1.0000 5.000 1.1935 0.01175 0.00547 -0.1399 0.5448 1.0000 5.500 1.2427 0.01220 0.00602 -0.1387 0.5304 1.0000 6.000 1.2878 0.01267 0.00644 -0.1366 0.5080 1.0000 6.500 1.3228 0.01305 0.00682 -0.1325 0.4730 1.0000 7.000 1.3585 0.01354 0.00734 -0.1286 0.4397 1.0000 7.500 1.3921 0.01412 0.00797 -0.1244 0.4024 1.0000 8.000 1.4101 0.01513 0.00882 -0.1174 0.3380 1.0000 8.500 1.3992 0.01791 0.01082 -0.1066 0.2064 1.0000 9.000 1.3752 0.02227 0.01429 -0.0955 0.0740 1.0000 9.500 1.3720 0.02580 0.01770 -0.0881 0.0419 1.0000 10.000 1.3696 0.02962 0.02164 -0.0818 0.0342 1.0000 10.500 1.3793 0.03288 0.02514 -0.0775 0.0314 1.0000 11.000 1.3833 0.03690 0.02934 -0.0735 0.0289 1.0000 11.500 1.3824 0.04172 0.03431 -0.0699 0.0270 1.0000 12.000 1.3836 0.04681 0.03957 -0.0666 0.0253 1.0000 12.500 1.3973 0.05086 0.04386 -0.0643 0.0243 1.0000 13.000 1.4139 0.05490 0.04812 -0.0621 0.0231 1.0000 13.500 1.4323 0.05902 0.05246 -0.0602 0.0220 1.0000 14.000 1.4465 0.06361 0.05724 -0.0588 0.0207 1.0000 14.500 1.4719 0.06969 0.06365 -0.0567 0.0193 1.0000 15.000 1.4649 0.07723 0.07165 -0.0561 0.0190 1.0000 15.500 1.4496 0.08599 0.08088 -0.0566 0.0188 1.0000 16.000 1.4262 0.09629 0.09164 -0.0586 0.0186 1.0000 16.500 1.3969 0.10823 0.10403 -0.0626 0.0185 1.0000 17.000 1.3631 0.12182 0.11805 -0.0687 0.0185 1.0000 17.500 1.3266 0.13717 0.13378 -0.0771 0.0185 1.0000 18.000 1.2858 0.15513 0.15207 -0.0880 0.0189 1.0000 18.500 0.9074 0.22164 0.21955 -0.1260 0.0389 1.0000 19.000 0.9172 0.22872 0.22665 -0.1285 0.0363 1.0000 19.500 0.9265 0.23795 0.23590 -0.1304 0.0341 1.0000 20.000 0.9186 0.25065 0.24860 -0.1381 0.0309 1.0000 20.500 0.9257 0.25900 0.25698 -0.1413 0.0279 1.0000 21.000 0.9407 0.26497 0.26300 -0.1422 0.0264 1.0000 21.500 0.9445 0.27715 0.27519 -0.1459 0.0256 1.0000 22.000 0.9395 0.28927 0.28730 -0.1527 0.0233 1.0000 22.500 0.9466 0.29781 0.29588 -0.1558 0.0207 1.0000 23.000 0.9616 0.30585 0.30394 -0.1562 0.0192 1.0000 23.500 0.9598 0.31737 0.31547 -0.1616 0.0189 1.0000 24.000 0.9617 0.32892 0.32703 -0.1664 0.0166 1.0000 24.500 0.9675 0.33823 0.33637 -0.1695 0.0154 1.0000 25.000 0.9738 0.34687 0.34505 -0.1723 0.0147 1.0000 25.500 0.9853 0.35650 0.35471 -0.1733 0.0140 1.0000 26.000 0.9828 0.36848 0.36670 -0.1787 0.0136 1.0000 26.500 0.9869 0.37960 0.37784 -0.1824 0.0116 1.0000 27.000 0.9915 0.38932 0.38759 -0.1854 0.0111 1.0000 27.500 0.9966 0.39802 0.39633 -0.1879 0.0103 1.0000 28.000 1.0039 0.40839 0.40673 -0.1897 0.0100 1.0000 28.500 1.0047 0.41947 0.41783 -0.1935 0.0099 1.0000 29.000 1.0063 0.43169 0.43006 -0.1975 0.0094 1.0000