XFOIL Version 6.96 Calculated polar for: NACA 2418 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.500 -0.9321 0.10184 0.09609 -0.0527 1.0000 0.0487 -18.250 -0.9387 0.09722 0.09142 -0.0551 1.0000 0.0491 -18.000 -0.9434 0.09301 0.08716 -0.0572 1.0000 0.0497 -17.750 -0.9507 0.08837 0.08246 -0.0596 1.0000 0.0502 -17.500 -0.9593 0.08357 0.07757 -0.0620 1.0000 0.0508 -17.250 -0.9684 0.07877 0.07267 -0.0645 1.0000 0.0514 -17.000 -0.9772 0.07412 0.06790 -0.0668 1.0000 0.0520 -16.750 -0.9851 0.06970 0.06335 -0.0689 1.0000 0.0527 -16.500 -0.9924 0.06548 0.05899 -0.0709 1.0000 0.0534 -16.250 -0.9986 0.06152 0.05488 -0.0726 1.0000 0.0541 -16.000 -1.0011 0.05827 0.05161 -0.0738 1.0000 0.0546 -15.750 -1.0036 0.05505 0.04834 -0.0750 1.0000 0.0553 -15.500 -1.0057 0.05195 0.04516 -0.0761 1.0000 0.0559 -15.250 -1.0069 0.04902 0.04215 -0.0770 1.0000 0.0567 -15.000 -1.0073 0.04629 0.03933 -0.0776 1.0000 0.0576 -14.750 -1.0067 0.04377 0.03671 -0.0780 1.0000 0.0586 -14.500 -1.0049 0.04147 0.03428 -0.0781 1.0000 0.0597 -14.250 -1.0041 0.03928 0.03205 -0.0780 1.0000 0.0606 -14.000 -1.0027 0.03730 0.03004 -0.0776 1.0000 0.0615 -13.750 -1.0006 0.03557 0.02825 -0.0768 1.0000 0.0627 -13.500 -0.9983 0.03404 0.02665 -0.0755 1.0000 0.0640 -13.250 -0.9964 0.03270 0.02522 -0.0737 1.0000 0.0653 -13.000 -0.9964 0.03147 0.02394 -0.0714 1.0000 0.0665 -12.750 -0.9988 0.03038 0.02284 -0.0684 1.0000 0.0675 -12.500 -1.0021 0.02948 0.02191 -0.0648 1.0000 0.0687 -12.250 -1.0074 0.02874 0.02113 -0.0605 1.0000 0.0699 -12.000 -1.0154 0.02814 0.02047 -0.0554 1.0000 0.0710 -11.750 -1.0259 0.02767 0.01994 -0.0495 1.0000 0.0722 -11.500 -1.0200 0.02700 0.01924 -0.0467 0.9985 0.0738 -11.250 -0.9940 0.02619 0.01840 -0.0477 0.9947 0.0764 -11.000 -0.9660 0.02549 0.01761 -0.0487 0.9913 0.0796 -10.750 -0.9405 0.02474 0.01686 -0.0492 0.9866 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0.00443 -0.0484 0.6493 0.5417 -0.500 0.1758 0.01207 0.00442 -0.0478 0.6380 0.5662 -0.250 0.2016 0.01205 0.00443 -0.0472 0.6263 0.5897 0.000 0.2274 0.01203 0.00445 -0.0466 0.6153 0.6124 0.250 0.2531 0.01204 0.00447 -0.0459 0.6042 0.6350 0.500 0.2789 0.01204 0.00452 -0.0453 0.5934 0.6575 0.750 0.3046 0.01207 0.00456 -0.0446 0.5833 0.6795 1.000 0.3303 0.01209 0.00464 -0.0440 0.5726 0.7019 1.500 0.3808 0.01220 0.00481 -0.0424 0.5501 0.7480 1.750 0.4060 0.01228 0.00491 -0.0416 0.5388 0.7706 2.000 0.4314 0.01237 0.00504 -0.0409 0.5280 0.7936 2.250 0.4573 0.01249 0.00518 -0.0402 0.5189 0.8161 2.500 0.4835 0.01261 0.00533 -0.0395 0.5093 0.8379 2.750 0.5101 0.01277 0.00548 -0.0390 0.5004 0.8586 3.000 0.5377 0.01293 0.00566 -0.0387 0.4909 0.8791 3.250 0.5663 0.01314 0.00584 -0.0385 0.4823 0.8993 3.500 0.5969 0.01332 0.00605 -0.0389 0.4723 0.9181 3.750 0.6279 0.01356 0.00624 -0.0393 0.4629 0.9342 4.000 0.6604 0.01375 0.00645 -0.0402 0.4529 0.9472 4.250 0.6953 0.01400 0.00664 -0.0417 0.4431 0.9565 4.500 0.7282 0.01420 0.00684 -0.0427 0.4321 0.9665 4.750 0.7642 0.01445 0.00704 -0.0445 0.4214 0.9738 5.000 0.7989 0.01469 0.00725 -0.0461 0.4087 0.9811 5.250 0.8351 0.01495 0.00746 -0.0481 0.3939 0.9872 5.500 0.8696 0.01523 0.00769 -0.0498 0.3794 0.9935 5.750 0.9049 0.01553 0.00793 -0.0516 0.3661 0.9990 6.000 0.9224 0.01574 0.00811 -0.0499 0.3551 1.0000 6.250 0.9353 0.01597 0.00830 -0.0471 0.3453 1.0000 6.500 0.9478 0.01621 0.00850 -0.0444 0.3349 1.0000 6.750 0.9612 0.01646 0.00873 -0.0417 0.3251 1.0000 7.000 0.9729 0.01676 0.00897 -0.0388 0.3150 1.0000 7.250 0.9865 0.01703 0.00923 -0.0362 0.3048 1.0000 7.500 0.9982 0.01739 0.00953 -0.0334 0.2951 1.0000 7.750 1.0113 0.01771 0.00984 -0.0308 0.2845 1.0000 8.000 1.0225 0.01809 0.01018 -0.0279 0.2748 1.0000 8.250 1.0344 0.01851 0.01056 -0.0253 0.2642 1.0000 8.500 1.0479 0.01896 0.01099 -0.0230 0.2539 1.0000 8.750 1.0598 0.01951 0.01148 -0.0206 0.2441 1.0000 9.000 1.0742 0.02002 0.01200 -0.0187 0.2339 1.0000 9.250 1.0872 0.02064 0.01258 -0.0167 0.2248 1.0000 9.500 1.1002 0.02129 0.01321 -0.0148 0.2152 1.0000 9.750 1.1138 0.02196 0.01388 -0.0130 0.2063 1.0000 10.000 1.1251 0.02276 0.01464 -0.0111 0.1974 1.0000 10.250 1.1391 0.02349 0.01539 -0.0096 0.1883 1.0000 10.500 1.1501 0.02439 0.01627 -0.0079 0.1799 1.0000 10.750 1.1624 0.02527 0.01716 -0.0064 0.1709 1.0000 11.000 1.1735 0.02625 0.01814 -0.0049 0.1628 1.0000 11.250 1.1830 0.02737 0.01925 -0.0034 0.1548 1.0000 11.500 1.1937 0.02847 0.02036 -0.0021 0.1473 1.0000 11.750 1.2014 0.02980 0.02169 -0.0007 0.1406 1.0000 12.000 1.2110 0.03107 0.02299 0.0004 0.1339 1.0000 12.250 1.2173 0.03261 0.02453 0.0016 0.1284 1.0000 12.500 1.2257 0.03406 0.02602 0.0026 0.1227 1.0000 12.750 1.2300 0.03588 0.02784 0.0037 0.1179 1.0000 13.000 1.2377 0.03748 0.02951 0.0045 0.1132 1.0000 13.250 1.2419 0.03943 0.03148 0.0052 0.1089 1.0000 13.500 1.2467 0.04140 0.03350 0.0059 0.1051 1.0000 13.750 1.2514 0.04342 0.03558 0.0064 0.1012 1.0000 14.000 1.2527 0.04583 0.03802 0.0068 0.0978 1.0000 14.250 1.2573 0.04800 0.04027 0.0071 0.0944 1.0000 14.500 1.2598 0.05045 0.04277 0.0073 0.0911 1.0000 15.000 1.2625 0.05573 0.04817 0.0074 0.0853 1.0000 15.250 1.2631 0.05856 0.05106 0.0072 0.0826 1.0000 15.500 1.2613 0.06173 0.05428 0.0069 0.0804 1.0000 15.750 1.2624 0.06460 0.05723 0.0066 0.0781 1.0000 16.000 1.2623 0.06764 0.06036 0.0062 0.0759 1.0000 16.250 1.2604 0.07098 0.06375 0.0056 0.0740 1.0000 16.500 1.2569 0.07456 0.06736 0.0049 0.0724 1.0000 16.750 1.2570 0.07771 0.07062 0.0043 0.0705 1.0000 17.000 1.2557 0.08108 0.07408 0.0035 0.0688 1.0000 17.250 1.2529 0.08471 0.07777 0.0026 0.0672 1.0000 17.500 1.2488 0.08854 0.08163 0.0016 0.0659 1.0000