XFOIL Version 6.94 Calculated polar for: CLARK X 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 0.3981 0.00821 0.00341 -0.0877 0.7753 0.9783 0.500 0.4841 0.00823 0.00326 -0.0940 0.7557 1.0000 1.000 0.5336 0.00833 0.00320 -0.0927 0.7349 1.0000 1.500 0.5831 0.00846 0.00320 -0.0912 0.7134 1.0000 2.000 0.6320 0.00861 0.00322 -0.0896 0.6887 1.0000 2.500 0.6801 0.00879 0.00328 -0.0878 0.6607 1.0000 3.000 0.7245 0.00901 0.00329 -0.0851 0.6136 1.0000 3.500 0.7700 0.00934 0.00343 -0.0829 0.5690 1.0000 4.000 0.8150 0.00979 0.00366 -0.0806 0.5206 1.0000 4.500 0.8552 0.01053 0.00399 -0.0775 0.4438 1.0000 5.000 0.8977 0.01128 0.00450 -0.0751 0.3823 1.0000 5.500 0.9313 0.01267 0.00523 -0.0715 0.2732 1.0000 6.000 0.9703 0.01384 0.00599 -0.0689 0.2021 1.0000 6.500 1.0101 0.01497 0.00685 -0.0665 0.1516 1.0000 7.000 1.0316 0.01746 0.00859 -0.0615 0.0323 1.0000 7.500 1.0685 0.01868 0.00978 -0.0586 0.0104 1.0000 8.000 1.1053 0.01968 0.01085 -0.0556 0.0078 1.0000 8.500 1.1401 0.02083 0.01214 -0.0523 0.0072 1.0000 9.000 1.1719 0.02221 0.01373 -0.0489 0.0069 1.0000 9.500 1.1992 0.02395 0.01572 -0.0452 0.0068 1.0000 10.000 1.2204 0.02619 0.01824 -0.0412 0.0068 1.0000 10.500 1.2346 0.02908 0.02144 -0.0371 0.0068 1.0000 11.000 1.2429 0.03266 0.02528 -0.0333 0.0069 1.0000 11.500 1.2470 0.03692 0.02979 -0.0300 0.0069 1.0000 12.000 1.2488 0.04172 0.03484 -0.0275 0.0070 1.0000 12.500 1.2495 0.04694 0.04029 -0.0255 0.0071 1.0000 13.000 1.2497 0.05246 0.04605 -0.0240 0.0072 1.0000 13.500 1.2496 0.05831 0.05215 -0.0229 0.0073 1.0000 14.000 1.2479 0.06465 0.05879 -0.0223 0.0074 1.0000 14.500 1.2433 0.07170 0.06613 -0.0223 0.0075 1.0000 15.000 1.2343 0.07974 0.07448 -0.0233 0.0075 1.0000 15.500 1.2217 0.08882 0.08389 -0.0254 0.0075 1.0000 16.000 1.2048 0.09916 0.09457 -0.0288 0.0075 1.0000 16.500 1.1840 0.11087 0.10663 -0.0339 0.0075 1.0000 17.000 1.1625 0.12362 0.11973 -0.0404 0.0077 1.0000 17.500 1.1358 0.13848 0.13494 -0.0490 0.0078 1.0000 18.000 1.0989 0.15758 0.15443 -0.0610 0.0082 1.0000 18.500 0.9996 0.20493 0.20210 -0.0883 0.0110 1.0000 19.000 1.0046 0.21503 0.21218 -0.0939 0.0123 1.0000 19.500 0.7198 0.20049 0.19788 -0.0604 0.0118 1.0000