FX 72-LS-160 (fx72ls160-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 72-LS-160 (fx72ls160-il) Reynolds number: 1,000,000 Max Cl/Cd: 175.13 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx72ls160-il-1000000.txt Download as CSV file: xf-fx72ls160-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 0.2339 0.08603 0.08260 -0.1315 0.6478 0.0106
-10.250 0.2404 0.08313 0.07970 -0.1326 0.6464 0.0109
-10.000 0.2468 0.08019 0.07677 -0.1336 0.6460 0.0111
-9.750 0.2529 0.07718 0.07377 -0.1347 0.6454 0.0114
-9.500 0.2549 0.07351 0.07013 -0.1360 0.6449 0.0117
-9.250 0.2558 0.06971 0.06635 -0.1375 0.6442 0.0118
-9.000 0.2597 0.06641 0.06306 -0.1386 0.6434 0.0119
-8.750 0.2634 0.06313 0.05980 -0.1397 0.6425 0.0119
-8.500 0.2667 0.05994 0.05663 -0.1404 0.6415 0.0120
-8.250 0.2728 0.05743 0.05413 -0.1410 0.6405 0.0121
-8.000 0.2799 0.05509 0.05181 -0.1417 0.6394 0.0122
-7.750 0.2850 0.05249 0.04922 -0.1425 0.6384 0.0123
-7.500 0.2915 0.05027 0.04701 -0.1431 0.6374 0.0125
-7.250 0.2950 0.04758 0.04434 -0.1440 0.6364 0.0127
-7.000 0.2975 0.04491 0.04168 -0.1449 0.6353 0.0130
-6.750 0.2972 0.04208 0.03887 -0.1457 0.6342 0.0132
-6.500 0.2910 0.03932 0.03613 -0.1462 0.6329 0.0135
-6.250 0.2890 0.03602 0.03283 -0.1493 0.6314 0.0135
-6.000 0.2382 0.02165 0.01723 -0.1770 0.6337 0.0123
-5.750 0.2568 0.01749 0.01245 -0.1775 0.6323 0.0110
-5.500 0.2829 0.01618 0.01081 -0.1779 0.6305 0.0113
-5.250 0.3104 0.01534 0.00975 -0.1782 0.6293 0.0116
-5.000 0.3384 0.01469 0.00893 -0.1786 0.6287 0.0118
-4.500 0.3944 0.01320 0.00716 -0.1792 0.6270 0.0120
-4.250 0.4225 0.01240 0.00628 -0.1796 0.6259 0.0122
-4.000 0.4509 0.01189 0.00574 -0.1800 0.6247 0.0126
-3.750 0.4797 0.01154 0.00536 -0.1804 0.6235 0.0132
-3.500 0.5088 0.01123 0.00501 -0.1809 0.6224 0.0137
-3.250 0.5380 0.01093 0.00467 -0.1813 0.6212 0.0141
-3.000 0.5673 0.01070 0.00440 -0.1817 0.6201 0.0145
-2.750 0.5968 0.01033 0.00399 -0.1823 0.6190 0.0153
-2.500 0.6262 0.01014 0.00379 -0.1828 0.6179 0.0160
-2.250 0.6556 0.01002 0.00363 -0.1832 0.6166 0.0166
-2.000 0.6851 0.00995 0.00352 -0.1837 0.6151 0.0172
-1.750 0.7147 0.00994 0.00349 -0.1843 0.6131 0.0187
-1.500 0.7440 0.00981 0.00339 -0.1847 0.6124 0.0217
-1.250 0.7734 0.00965 0.00331 -0.1853 0.6115 0.0413
-1.000 0.8027 0.00956 0.00329 -0.1858 0.6105 0.0619
-0.750 0.8319 0.00949 0.00328 -0.1863 0.6094 0.0754
-0.500 0.8612 0.00943 0.00327 -0.1868 0.6082 0.0927
-0.250 0.8906 0.00935 0.00326 -0.1874 0.6069 0.1180
0.000 0.9203 0.00921 0.00327 -0.1881 0.6057 0.1753
0.250 0.9507 0.00897 0.00330 -0.1891 0.6043 0.2860
0.500 0.9825 0.00857 0.00338 -0.1906 0.6030 0.4912
0.750 1.0153 0.00807 0.00353 -0.1922 0.6017 0.7581
1.000 1.0393 0.00801 0.00369 -0.1913 0.6003 0.8715
1.250 1.0640 0.00811 0.00380 -0.1907 0.5987 0.9043
1.500 1.0895 0.00824 0.00392 -0.1903 0.5970 0.9198
1.750 1.1136 0.00826 0.00396 -0.1896 0.5961 0.9324
2.000 1.1352 0.00827 0.00399 -0.1884 0.5950 0.9457
2.250 1.1501 0.00822 0.00398 -0.1856 0.5937 0.9639
2.500 1.1693 0.00816 0.00394 -0.1838 0.5922 0.9869
2.750 1.2008 0.00819 0.00396 -0.1849 0.5907 1.0000
3.000 1.2309 0.00825 0.00400 -0.1858 0.5891 1.0000
3.250 1.2609 0.00832 0.00406 -0.1866 0.5877 1.0000
3.500 1.2908 0.00839 0.00412 -0.1874 0.5863 1.0000
3.750 1.3205 0.00849 0.00419 -0.1881 0.5848 1.0000
4.000 1.3504 0.00863 0.00430 -0.1890 0.5830 1.0000
4.250 1.3799 0.00878 0.00445 -0.1897 0.5813 1.0000
4.500 1.4083 0.00885 0.00454 -0.1903 0.5800 1.0000
4.750 1.4366 0.00892 0.00464 -0.1908 0.5784 1.0000
5.000 1.4649 0.00900 0.00474 -0.1913 0.5768 1.0000
5.250 1.4931 0.00909 0.00485 -0.1918 0.5751 1.0000
5.500 1.5212 0.00917 0.00494 -0.1923 0.5733 1.0000
5.750 1.5488 0.00924 0.00501 -0.1927 0.5713 1.0000
6.000 1.5763 0.00933 0.00510 -0.1931 0.5688 1.0000
6.250 1.6040 0.00948 0.00524 -0.1935 0.5660 1.0000
6.500 1.6292 0.00955 0.00536 -0.1935 0.5637 1.0000
6.750 1.6543 0.00960 0.00546 -0.1934 0.5605 1.0000
7.000 1.6790 0.00966 0.00553 -0.1932 0.5568 1.0000
7.250 1.7033 0.00978 0.00563 -0.1930 0.5526 1.0000
7.500 1.7264 0.00990 0.00579 -0.1925 0.5487 1.0000
7.750 1.7478 0.00998 0.00592 -0.1917 0.5430 1.0000
8.000 1.7655 0.01017 0.00607 -0.1903 0.5370 1.0000
8.250 1.7839 0.01032 0.00628 -0.1889 0.5312 1.0000
8.500 1.8009 0.01053 0.00651 -0.1873 0.5258 1.0000
8.750 1.8160 0.01084 0.00681 -0.1855 0.5212 1.0000
9.000 1.8342 0.01108 0.00711 -0.1843 0.5156 1.0000
9.250 1.8446 0.01152 0.00754 -0.1817 0.5080 1.0000
9.500 1.8583 0.01193 0.00799 -0.1798 0.5006 1.0000
9.750 1.8661 0.01256 0.00861 -0.1771 0.4928 1.0000
10.000 1.8756 0.01320 0.00929 -0.1747 0.4838 1.0000
10.250 1.8778 0.01420 0.01028 -0.1714 0.4737 1.0000
10.500 1.8770 0.01547 0.01154 -0.1680 0.4618 1.0000
10.750 1.8782 0.01680 0.01288 -0.1651 0.4501 1.0000
11.000 1.8702 0.01880 0.01487 -0.1613 0.4350 1.0000
11.250 1.8556 0.02142 0.01745 -0.1571 0.4178 1.0000
11.500 1.8347 0.02467 0.02065 -0.1526 0.3989 1.0000
11.750 1.8102 0.02836 0.02427 -0.1480 0.3775 1.0000
12.000 1.7864 0.03221 0.02805 -0.1439 0.3574 1.0000
12.250 1.7650 0.03610 0.03186 -0.1402 0.3384 1.0000
12.500 1.7497 0.03965 0.03535 -0.1373 0.3196 1.0000
12.750 1.7368 0.04314 0.03878 -0.1348 0.3008 1.0000
13.000 1.7245 0.04668 0.04223 -0.1325 0.2802 1.0000
13.500 1.7014 0.05404 0.04942 -0.1286 0.2403 1.0000
13.750 1.6923 0.05761 0.05289 -0.1269 0.2188 1.0000
14.000 1.6848 0.06115 0.05635 -0.1255 0.2011 1.0000
14.250 1.6782 0.06464 0.05972 -0.1243 0.1800 1.0000
14.500 1.6757 0.06777 0.06281 -0.1234 0.1664 1.0000
14.750 1.6727 0.07101 0.06597 -0.1225 0.1491 1.0000
15.000 1.6689 0.07444 0.06932 -0.1218 0.1337 1.0000
15.250 1.6669 0.07767 0.07248 -0.1211 0.1195 1.0000
15.750 1.6651 0.08407 0.07878 -0.1202 0.0953 1.0000
16.000 1.6656 0.08714 0.08180 -0.1199 0.0841 1.0000
16.250 1.6645 0.09049 0.08511 -0.1196 0.0737 1.0000
16.500 1.6642 0.09371 0.08829 -0.1195 0.0630 1.0000
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