XFOIL Version 6.96 Calculated polar for: CLARK K AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.000 -1.0913 0.04829 0.04566 -0.0822 1.0000 0.0143 -15.750 -1.1295 0.03949 0.03656 -0.0907 1.0000 0.0142 -15.500 -1.1513 0.03531 0.03217 -0.0915 1.0000 0.0144 -15.250 -1.1659 0.03250 0.02919 -0.0893 1.0000 0.0148 -15.000 -1.1696 0.03002 0.02655 -0.0874 1.0000 0.0154 -14.750 -1.1686 0.02800 0.02439 -0.0853 1.0000 0.0160 -14.500 -1.1666 0.02619 0.02245 -0.0828 1.0000 0.0167 -14.250 -1.1634 0.02458 0.02074 -0.0801 1.0000 0.0177 -14.000 -1.1437 0.02300 0.01906 -0.0804 0.9982 0.0192 -13.750 -1.1195 0.02175 0.01775 -0.0812 0.9962 0.0211 -13.500 -1.0924 0.02088 0.01682 -0.0822 0.9945 0.0233 -13.250 -1.0607 0.02094 0.01696 -0.0831 0.9932 0.0252 -13.000 -1.0331 0.02048 0.01647 -0.0837 0.9908 0.0269 -12.750 -1.0043 0.02004 0.01598 -0.0844 0.9886 0.0280 -12.500 -0.9705 0.02058 0.01659 -0.0853 0.9870 0.0287 -12.250 -0.9373 0.02099 0.01703 -0.0862 0.9853 0.0294 -12.000 -0.9088 0.02057 0.01656 -0.0868 0.9826 0.0305 -11.750 -0.8859 0.01927 0.01510 -0.0869 0.9782 0.0317 -11.500 -0.8602 0.01818 0.01384 -0.0874 0.9748 0.0325 -11.250 -0.8324 0.01797 0.01359 -0.0877 0.9707 0.0329 -11.000 -0.8032 0.01810 0.01373 -0.0879 0.9663 0.0333 -10.750 -0.7734 0.01821 0.01382 -0.0883 0.9624 0.0336 -10.500 -0.7462 0.01830 0.01390 -0.0882 0.9565 0.0339 -10.250 -0.7182 0.01838 0.01396 -0.0882 0.9512 0.0342 -10.000 -0.6914 0.01842 0.01397 -0.0881 0.9451 0.0345 -9.750 -0.6649 0.01835 0.01385 -0.0879 0.9387 0.0349 -9.500 -0.6390 0.01817 0.01361 -0.0877 0.9322 0.0354 -9.250 -0.6134 0.01786 0.01322 -0.0874 0.9251 0.0360 -9.000 -0.5884 0.01733 0.01259 -0.0871 0.9180 0.0368 -8.750 -0.5633 0.01682 0.01196 -0.0868 0.9103 0.0374 -8.500 -0.5379 0.01634 0.01137 -0.0865 0.9030 0.0378 -8.250 -0.5121 0.01595 0.01088 -0.0862 0.8946 0.0381 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0.0439 -3.000 0.0499 0.00956 0.00328 -0.0825 0.7148 0.0442 -2.750 0.0773 0.00942 0.00311 -0.0824 0.7065 0.0444 -2.500 0.1048 0.00929 0.00295 -0.0823 0.6974 0.0446 -2.250 0.1323 0.00917 0.00280 -0.0822 0.6886 0.0448 -2.000 0.1598 0.00907 0.00266 -0.0821 0.6787 0.0449 -1.750 0.1872 0.00893 0.00249 -0.0820 0.6688 0.0451 -1.500 0.2140 0.00873 0.00225 -0.0817 0.6581 0.0456 -1.250 0.2413 0.00860 0.00209 -0.0816 0.6464 0.0460 -1.000 0.2684 0.00853 0.00197 -0.0814 0.6315 0.0464 -0.750 0.2951 0.00852 0.00189 -0.0811 0.6110 0.0468 -0.500 0.3218 0.00852 0.00182 -0.0809 0.5906 0.0472 -0.250 0.3490 0.00851 0.00176 -0.0807 0.5756 0.0477 0.000 0.3763 0.00850 0.00172 -0.0805 0.5622 0.0482 0.250 0.4036 0.00851 0.00168 -0.0804 0.5479 0.0488 0.500 0.4309 0.00852 0.00166 -0.0802 0.5349 0.0496 0.750 0.4582 0.00854 0.00165 -0.0801 0.5231 0.0504 1.000 0.4853 0.00858 0.00165 -0.0799 0.5097 0.0510 1.250 0.5124 0.00862 0.00165 -0.0798 0.4952 0.0516 1.500 0.5398 0.00866 0.00167 -0.0796 0.4828 0.0520 1.750 0.5670 0.00871 0.00169 -0.0795 0.4708 0.0524 2.000 0.5940 0.00877 0.00172 -0.0793 0.4569 0.0528 2.250 0.6207 0.00884 0.00174 -0.0791 0.4411 0.0539 2.500 0.6475 0.00893 0.00178 -0.0789 0.4257 0.0550 2.750 0.6742 0.00903 0.00184 -0.0787 0.4111 0.0562 3.000 0.7008 0.00914 0.00191 -0.0784 0.3955 0.0575 3.250 0.7271 0.00928 0.00200 -0.0782 0.3777 0.0591 3.500 0.7533 0.00944 0.00210 -0.0779 0.3590 0.0610 3.750 0.7794 0.00959 0.00222 -0.0776 0.3425 0.0670 4.000 0.8050 0.00954 0.00236 -0.0773 0.3273 0.1960 4.250 0.8279 0.00884 0.00260 -0.0770 0.3130 0.5941 4.500 0.8480 0.00818 0.00287 -0.0752 0.2983 0.9670 4.750 0.8867 0.00849 0.00307 -0.0778 0.2747 1.0000 5.000 0.9102 0.00879 0.00326 -0.0770 0.2537 1.0000 5.250 0.9347 0.00904 0.00344 -0.0764 0.2398 1.0000 5.500 0.9593 0.00928 0.00362 -0.0759 0.2276 1.0000 5.750 0.9834 0.00956 0.00383 -0.0752 0.2126 1.0000 6.000 1.0074 0.00986 0.00405 -0.0746 0.1980 1.0000 6.250 1.0313 0.01016 0.00428 -0.0740 0.1832 1.0000 6.500 1.0551 0.01047 0.00452 -0.0733 0.1694 1.0000 6.750 1.0783 0.01083 0.00479 -0.0726 0.1525 1.0000 7.000 1.1006 0.01125 0.00510 -0.0717 0.1326 1.0000 7.250 1.1203 0.01186 0.00554 -0.0705 0.1031 1.0000 7.500 1.1380 0.01263 0.00610 -0.0690 0.0695 1.0000 7.750 1.1534 0.01356 0.00680 -0.0671 0.0347 1.0000 8.000 1.1748 0.01400 0.00722 -0.0661 0.0277 1.0000 8.250 1.1963 0.01442 0.00762 -0.0651 0.0241 1.0000 8.500 1.2183 0.01479 0.00799 -0.0643 0.0220 1.0000 8.750 1.2396 0.01518 0.00839 -0.0633 0.0202 1.0000 9.000 1.2599 0.01563 0.00885 -0.0622 0.0184 1.0000 9.250 1.2806 0.01601 0.00924 -0.0611 0.0176 1.0000 9.500 1.2995 0.01641 0.00966 -0.0597 0.0165 1.0000 9.750 1.3174 0.01688 0.01014 -0.0582 0.0155 1.0000 10.000 1.3346 0.01739 0.01067 -0.0567 0.0145 1.0000 10.250 1.3526 0.01785 0.01116 -0.0553 0.0139 1.0000 10.500 1.3698 0.01836 0.01170 -0.0538 0.0133 1.0000 10.750 1.3862 0.01893 0.01229 -0.0523 0.0127 1.0000 11.000 1.4017 0.01955 0.01294 -0.0507 0.0122 1.0000 11.250 1.4160 0.02026 0.01368 -0.0491 0.0116 1.0000 11.500 1.4315 0.02091 0.01438 -0.0476 0.0113 1.0000 11.750 1.4463 0.02161 0.01512 -0.0461 0.0109 1.0000 12.000 1.4605 0.02237 0.01592 -0.0447 0.0105 1.0000 12.250 1.4737 0.02321 0.01680 -0.0432 0.0101 1.0000 12.500 1.4861 0.02414 0.01777 -0.0417 0.0097 1.0000 12.750 1.4971 0.02519 0.01886 -0.0402 0.0094 1.0000 13.000 1.5071 0.02635 0.02007 -0.0387 0.0091 1.0000 13.250 1.5181 0.02746 0.02125 -0.0374 0.0089 1.0000 13.500 1.5282 0.02867 0.02252 -0.0361 0.0087 1.0000 13.750 1.5375 0.02999 0.02391 -0.0349 0.0085 1.0000 14.000 1.5460 0.03142 0.02540 -0.0337 0.0083 1.0000 14.250 1.5535 0.03296 0.02701 -0.0326 0.0081 1.0000 14.500 1.5600 0.03464 0.02876 -0.0316 0.0080 1.0000 14.750 1.5657 0.03645 0.03064 -0.0306 0.0078 1.0000 15.000 1.5702 0.03843 0.03268 -0.0298 0.0076 1.0000 15.250 1.5732 0.04060 0.03492 -0.0290 0.0075 1.0000 15.500 1.5744 0.04304 0.03744 -0.0283 0.0073 1.0000 15.750 1.5731 0.04585 0.04034 -0.0278 0.0071 1.0000 16.000 1.5738 0.04852 0.04309 -0.0275 0.0070 1.0000 16.250 1.5741 0.05134 0.04600 -0.0274 0.0069 1.0000 16.500 1.5732 0.05439 0.04914 -0.0274 0.0068 1.0000 16.750 1.5705 0.05776 0.05261 -0.0276 0.0068 1.0000 17.000 1.5668 0.06132 0.05627 -0.0280 0.0067 1.0000 17.250 1.5614 0.06523 0.06028 -0.0286 0.0066 1.0000 17.500 1.5550 0.06938 0.06454 -0.0294 0.0065 1.0000 17.750 1.5473 0.07379 0.06906 -0.0304 0.0064 1.0000 18.000 1.5381 0.07849 0.07386 -0.0315 0.0064 1.0000 18.250 1.5275 0.08349 0.07897 -0.0329 0.0063 1.0000 18.500 1.5157 0.08878 0.08438 -0.0345 0.0063 1.0000 18.750 1.5030 0.09428 0.08999 -0.0362 0.0062 1.0000 19.000 1.4896 0.09996 0.09578 -0.0382 0.0062 1.0000 19.250 1.4751 0.10594 0.10188 -0.0404 0.0061 1.0000