FX 72-LS-160 (fx72ls160-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 72-LS-160 (fx72ls160-il) Reynolds number: 1,000,000 Max Cl/Cd: 174.27 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx72ls160-il-1000000-n5.txt Download as CSV file: xf-fx72ls160-il-1000000-n5.csv |
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
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Polar data table (+)
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