XFOIL Version 6.96 Calculated polar for: FX 72-LS-160 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 ------ -------- --------- --------- -------- -------- -------- -10.500 0.2030 0.09385 0.09004 -0.1401 0.6292 0.0080 -10.250 0.2094 0.09100 0.08721 -0.1413 0.6287 0.0079 -10.000 0.2101 0.08667 0.08289 -0.1427 0.6282 0.0068 -9.750 0.2190 0.08454 0.08078 -0.1437 0.6275 0.0067 -9.500 0.2258 0.08204 0.07830 -0.1447 0.6267 0.0066 -9.250 0.2317 0.07940 0.07568 -0.1457 0.6258 0.0064 -8.250 -0.0019 0.02292 0.01863 -0.1730 0.6224 0.0060 -8.000 0.0158 0.02055 0.01595 -0.1736 0.6213 0.0062 -7.750 0.0372 0.01891 0.01405 -0.1740 0.6202 0.0063 -7.500 0.0609 0.01770 0.01263 -0.1742 0.6192 0.0065 -7.250 0.0859 0.01675 0.01149 -0.1745 0.6180 0.0067 -7.000 0.1119 0.01600 0.01059 -0.1747 0.6167 0.0068 -6.750 0.1383 0.01535 0.00979 -0.1750 0.6154 0.0069 -6.500 0.1652 0.01479 0.00909 -0.1752 0.6140 0.0070 -6.250 0.1925 0.01429 0.00848 -0.1755 0.6129 0.0070 -6.000 0.2197 0.01353 0.00760 -0.1759 0.6122 0.0072 -5.750 0.2475 0.01297 0.00695 -0.1763 0.6114 0.0073 -5.500 0.2758 0.01256 0.00648 -0.1767 0.6104 0.0075 -5.250 0.3042 0.01221 0.00609 -0.1770 0.6093 0.0076 -5.000 0.3328 0.01188 0.00571 -0.1774 0.6082 0.0078 -4.750 0.3615 0.01160 0.00538 -0.1778 0.6071 0.0081 -4.500 0.3903 0.01135 0.00509 -0.1782 0.6060 0.0084 -4.250 0.4192 0.01112 0.00481 -0.1786 0.6049 0.0088 -4.000 0.4481 0.01090 0.00454 -0.1789 0.6037 0.0091 -3.750 0.4770 0.01070 0.00430 -0.1793 0.6024 0.0093 -3.500 0.5059 0.01039 0.00394 -0.1798 0.6011 0.0097 -3.250 0.5348 0.01015 0.00367 -0.1802 0.5998 0.0100 -3.000 0.5637 0.00999 0.00348 -0.1806 0.5985 0.0104 -2.750 0.5926 0.00987 0.00332 -0.1810 0.5972 0.0107 -2.500 0.6220 0.00972 0.00317 -0.1815 0.5964 0.0111 -2.250 0.6513 0.00960 0.00304 -0.1819 0.5956 0.0114 -2.000 0.6806 0.00950 0.00294 -0.1824 0.5945 0.0118 -1.750 0.7099 0.00938 0.00281 -0.1829 0.5934 0.0126 -1.500 0.7393 0.00929 0.00271 -0.1833 0.5920 0.0134 -1.250 0.7685 0.00922 0.00264 -0.1838 0.5906 0.0143 -0.750 0.8270 0.00904 0.00254 -0.1848 0.5880 0.0388 -0.500 0.8561 0.00898 0.00253 -0.1853 0.5867 0.0530 -0.250 0.8850 0.00896 0.00252 -0.1857 0.5855 0.0637 0.000 0.9138 0.00893 0.00253 -0.1862 0.5841 0.0777 0.250 0.9426 0.00890 0.00255 -0.1866 0.5827 0.1010 0.500 0.9718 0.00883 0.00258 -0.1872 0.5813 0.1447 0.750 1.0016 0.00870 0.00263 -0.1880 0.5802 0.2115 1.000 1.0315 0.00857 0.00269 -0.1888 0.5789 0.2932 1.250 1.0626 0.00831 0.00279 -0.1901 0.5775 0.4466 1.500 1.0936 0.00812 0.00289 -0.1912 0.5761 0.5703 1.750 1.1251 0.00790 0.00301 -0.1924 0.5746 0.7153 2.000 1.1509 0.00776 0.00319 -0.1921 0.5731 0.8564 2.250 1.1755 0.00780 0.00329 -0.1916 0.5716 0.8917 2.500 1.2002 0.00786 0.00336 -0.1911 0.5701 0.9108 2.750 1.2240 0.00792 0.00342 -0.1904 0.5685 0.9261 3.000 1.2442 0.00798 0.00349 -0.1889 0.5666 0.9447 3.250 1.2564 0.00792 0.00350 -0.1855 0.5653 0.9704 3.500 1.2828 0.00793 0.00352 -0.1855 0.5638 1.0000 3.750 1.3122 0.00801 0.00361 -0.1862 0.5622 1.0000 4.000 1.3413 0.00810 0.00370 -0.1869 0.5605 1.0000 4.250 1.3701 0.00819 0.00380 -0.1875 0.5588 1.0000 4.500 1.3985 0.00829 0.00390 -0.1880 0.5569 1.0000 4.750 1.4264 0.00840 0.00400 -0.1884 0.5550 1.0000 5.000 1.4537 0.00853 0.00411 -0.1888 0.5530 1.0000 5.250 1.4808 0.00866 0.00424 -0.1891 0.5511 1.0000 5.500 1.5086 0.00876 0.00437 -0.1895 0.5496 1.0000 5.750 1.5360 0.00886 0.00450 -0.1899 0.5474 1.0000 6.000 1.5624 0.00898 0.00464 -0.1901 0.5443 1.0000 6.250 1.5876 0.00911 0.00478 -0.1900 0.5406 1.0000 6.500 1.6111 0.00929 0.00494 -0.1896 0.5369 1.0000 6.750 1.6363 0.00941 0.00510 -0.1896 0.5329 1.0000 7.000 1.6589 0.00958 0.00528 -0.1891 0.5271 1.0000 7.250 1.6762 0.00982 0.00549 -0.1875 0.5208 1.0000 7.500 1.6964 0.01001 0.00572 -0.1865 0.5145 1.0000 7.750 1.7091 0.01037 0.00604 -0.1842 0.5060 1.0000 8.000 1.7251 0.01070 0.00637 -0.1825 0.4968 1.0000 8.250 1.7341 0.01122 0.00687 -0.1797 0.4846 1.0000 8.500 1.7402 0.01190 0.00751 -0.1765 0.4722 1.0000 8.750 1.7442 0.01273 0.00831 -0.1732 0.4598 1.0000 9.000 1.7513 0.01355 0.00912 -0.1706 0.4489 1.0000 9.250 1.7539 0.01464 0.01021 -0.1675 0.4369 1.0000 9.500 1.7448 0.01648 0.01200 -0.1631 0.4187 1.0000 9.750 1.7278 0.01908 0.01453 -0.1583 0.3977 1.0000 10.000 1.7050 0.02236 0.01773 -0.1534 0.3737 1.0000 10.250 1.6813 0.02593 0.02122 -0.1487 0.3524 1.0000 10.500 1.6662 0.02900 0.02425 -0.1451 0.3349 1.0000 10.750 1.6441 0.03276 0.02792 -0.1412 0.3110 1.0000 11.000 1.6316 0.03597 0.03106 -0.1383 0.2930 1.0000 11.250 1.6205 0.03919 0.03421 -0.1357 0.2746 1.0000 11.500 1.6119 0.04231 0.03725 -0.1335 0.2556 1.0000 11.750 1.6055 0.04532 0.04019 -0.1316 0.2364 1.0000 12.000 1.5963 0.04870 0.04348 -0.1296 0.2162 1.0000 12.250 1.5940 0.05150 0.04619 -0.1281 0.1994 1.0000 12.500 1.5914 0.05442 0.04906 -0.1268 0.1839 1.0000 12.750 1.5910 0.05713 0.05170 -0.1257 0.1683 1.0000 13.000 1.5910 0.05990 0.05442 -0.1247 0.1545 1.0000 13.250 1.5918 0.06263 0.05709 -0.1238 0.1408 1.0000 13.500 1.5939 0.06524 0.05965 -0.1230 0.1278 1.0000 13.750 1.5951 0.06804 0.06242 -0.1222 0.1168 1.0000 14.000 1.5977 0.07067 0.06501 -0.1216 0.1054 1.0000 14.250 1.5982 0.07363 0.06790 -0.1210 0.0924 1.0000 14.500 1.6020 0.07624 0.07051 -0.1206 0.0852 1.0000 14.750 1.6052 0.07891 0.07314 -0.1201 0.0758 1.0000 15.000 1.6073 0.08178 0.07598 -0.1198 0.0666 1.0000 15.250 1.6092 0.08471 0.07888 -0.1194 0.0569 1.0000 15.500 1.6130 0.08741 0.08155 -0.1192 0.0494 1.0000