XFOIL Version 6.94 Calculated polar for: NASA/LANGLEY LS(1)-0413 (GA(W)- 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 0.5046 0.00895 0.00425 -0.1131 0.8098 0.7445 0.500 0.5607 0.00892 0.00420 -0.1126 0.7937 0.7522 1.000 0.6178 0.00888 0.00412 -0.1124 0.7731 0.7607 1.500 0.6765 0.00884 0.00408 -0.1129 0.7547 0.7661 2.000 0.7330 0.00883 0.00410 -0.1128 0.7326 0.7712 2.500 0.7893 0.00890 0.00413 -0.1126 0.7017 0.7771 3.000 0.8442 0.00910 0.00419 -0.1123 0.6455 0.7829 3.500 0.8866 0.01018 0.00454 -0.1097 0.4911 0.7888 4.000 0.9231 0.01191 0.00545 -0.1065 0.3236 0.7946 4.500 0.9654 0.01326 0.00626 -0.1046 0.2222 0.8016 5.000 1.0107 0.01432 0.00702 -0.1031 0.1652 0.8080 5.500 1.0557 0.01521 0.00780 -0.1013 0.1358 0.8144 6.000 1.1016 0.01605 0.00858 -0.0998 0.1170 0.8219 6.500 1.1458 0.01693 0.00944 -0.0980 0.1041 0.8296 7.000 1.1878 0.01783 0.01038 -0.0957 0.0942 0.8381 7.500 1.2294 0.01875 0.01133 -0.0935 0.0851 0.8470 8.000 1.2674 0.01960 0.01224 -0.0907 0.0765 0.8566 8.500 1.3019 0.02054 0.01324 -0.0872 0.0695 0.8675 9.000 1.3363 0.02162 0.01441 -0.0840 0.0634 0.8799 9.500 1.3678 0.02288 0.01576 -0.0805 0.0584 0.8940 10.000 1.3991 0.02407 0.01710 -0.0771 0.0537 0.9128 10.500 1.4243 0.02528 0.01850 -0.0726 0.0494 0.9522 11.500 1.4866 0.02882 0.02218 -0.0681 0.0409 1.0000 12.000 1.5155 0.03085 0.02431 -0.0658 0.0374 1.0000 12.500 1.5414 0.03313 0.02672 -0.0633 0.0344 1.0000 13.000 1.5601 0.03602 0.02970 -0.0605 0.0321 1.0000 13.500 1.5804 0.03885 0.03274 -0.0581 0.0300 1.0000 14.000 1.5927 0.04246 0.03648 -0.0555 0.0283 1.0000 14.500 1.6044 0.04630 0.04054 -0.0533 0.0268 1.0000 15.000 1.6128 0.05059 0.04504 -0.0514 0.0254 1.0000 15.500 1.6115 0.05627 0.05087 -0.0501 0.0242 1.0000 16.000 1.6162 0.06161 0.05649 -0.0495 0.0229 1.0000 16.500 1.6134 0.06824 0.06336 -0.0497 0.0217 1.0000 17.000 1.6007 0.07676 0.07209 -0.0512 0.0209 1.0000 17.500 1.5813 0.08690 0.08252 -0.0540 0.0204 1.0000 18.000 1.5582 0.09834 0.09429 -0.0584 0.0198 1.0000 18.500 1.5242 0.11228 0.10855 -0.0648 0.0196 1.0000 19.000 1.4850 0.12787 0.12446 -0.0730 0.0195 1.0000 19.500 1.4459 0.14406 0.14093 -0.0825 0.0193 1.0000 20.000 1.4106 0.16015 0.15728 -0.0927 0.0192 1.0000 20.500 1.3800 0.17596 0.17332 -0.1035 0.0189 1.0000 21.000 1.3526 0.19188 0.18945 -0.1150 0.0185 1.0000 21.500 1.3192 0.21059 0.20840 -0.1289 0.0184 1.0000