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 = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.6804 0.00850 0.00218 -0.1486 0.7094 0.2517 0.500 0.7307 0.00839 0.00223 -0.1475 0.6838 0.3576 1.000 0.7877 0.00732 0.00240 -0.1479 0.6586 1.0000 1.500 0.8378 0.00762 0.00249 -0.1465 0.6333 1.0000 2.000 0.8878 0.00796 0.00263 -0.1453 0.6105 1.0000 2.500 0.9381 0.00828 0.00284 -0.1441 0.5899 1.0000 3.000 0.9885 0.00863 0.00308 -0.1430 0.5718 1.0000 3.500 1.0389 0.00899 0.00338 -0.1419 0.5556 1.0000 4.000 1.0893 0.00938 0.00370 -0.1409 0.5411 1.0000 4.500 1.1395 0.00974 0.00407 -0.1398 0.5272 1.0000 5.000 1.1894 0.01010 0.00447 -0.1387 0.5139 1.0000 5.500 1.2368 0.01049 0.00488 -0.1371 0.4965 1.0000 6.000 1.2778 0.01090 0.00524 -0.1342 0.4648 1.0000 6.500 1.3179 0.01138 0.00568 -0.1312 0.4319 1.0000 7.000 1.3578 0.01191 0.00621 -0.1283 0.4006 1.0000 7.500 1.3873 0.01274 0.00688 -0.1234 0.3456 1.0000 8.000 1.3924 0.01482 0.00834 -0.1147 0.2329 1.0000 8.500 1.3805 0.01824 0.01090 -0.1043 0.0952 1.0000 9.000 1.3822 0.02108 0.01341 -0.0966 0.0398 1.0000 9.500 1.3950 0.02345 0.01583 -0.0909 0.0289 1.0000 10.000 1.4028 0.02633 0.01888 -0.0851 0.0251 1.0000 10.500 1.4162 0.02903 0.02176 -0.0808 0.0231 1.0000 11.000 1.4244 0.03237 0.02525 -0.0766 0.0213 1.0000 11.500 1.4219 0.03696 0.03001 -0.0723 0.0199 1.0000 12.000 1.4154 0.04241 0.03569 -0.0685 0.0191 1.0000 12.500 1.4239 0.04675 0.04025 -0.0662 0.0186 1.0000 13.000 1.4325 0.05131 0.04501 -0.0641 0.0178 1.0000 13.500 1.4426 0.05590 0.04979 -0.0626 0.0168 1.0000 14.000 1.4519 0.06075 0.05483 -0.0614 0.0160 1.0000 14.500 1.4600 0.06595 0.06020 -0.0604 0.0152 1.0000 15.000 1.4695 0.07135 0.06580 -0.0591 0.0145 1.0000 15.500 1.4710 0.07864 0.07350 -0.0581 0.0139 1.0000 16.000 1.4642 0.08632 0.08152 -0.0595 0.0134 1.0000 16.500 1.4532 0.09528 0.09086 -0.0615 0.0130 1.0000 17.000 1.4357 0.10581 0.10178 -0.0648 0.0126 1.0000 17.500 1.4126 0.11785 0.11421 -0.0698 0.0124 1.0000 18.000 1.3826 0.13192 0.12868 -0.0767 0.0123 1.0000 18.500 1.3467 0.14839 0.14554 -0.0862 0.0123 1.0000 19.000 1.3028 0.16862 0.16615 -0.0991 0.0126 1.0000 19.500 1.2405 0.19806 0.19593 -0.1185 0.0133 1.0000 20.000 0.9286 0.24873 0.24707 -0.1395 0.0212 1.0000 20.500 0.9402 0.25455 0.25293 -0.1414 0.0199 1.0000 21.000 0.9437 0.26599 0.26438 -0.1448 0.0191 1.0000 21.500 0.9412 0.27937 0.27777 -0.1512 0.0166 1.0000 22.000 0.9476 0.28813 0.28654 -0.1545 0.0153 1.0000 22.500 0.9577 0.29484 0.29329 -0.1566 0.0144 1.0000 23.000 0.9620 0.30664 0.30508 -0.1599 0.0139 1.0000 23.500 0.9622 0.31985 0.31830 -0.1653 0.0124 1.0000 24.000 0.9680 0.32936 0.32783 -0.1685 0.0111 1.0000