FX 72-LS-160 (fx72ls160-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 72-LS-160 (fx72ls160-il) Reynolds number: 500,000 Max Cl/Cd: 125.74 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx72ls160-il-500000-n5.txt Download as CSV file: xf-fx72ls160-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 0.2157 0.08874 0.08422 -0.1403 0.6454 0.0124
-9.500 0.2236 0.08642 0.08191 -0.1412 0.6446 0.0126
-9.250 0.2303 0.08384 0.07936 -0.1423 0.6437 0.0127
-9.000 0.2373 0.08141 0.07695 -0.1433 0.6427 0.0128
-8.500 0.2358 0.07331 0.06891 -0.1459 0.6407 0.0093
-8.250 0.2428 0.07118 0.06679 -0.1467 0.6394 0.0091
-8.000 0.2475 0.06864 0.06428 -0.1477 0.6382 0.0090
-7.750 0.2530 0.06637 0.06202 -0.1485 0.6370 0.0088
-7.500 0.2521 0.06312 0.05881 -0.1495 0.6359 0.0088
-7.250 0.2512 0.06017 0.05589 -0.1504 0.6349 0.0087
-7.000 0.2433 0.05714 0.05290 -0.1509 0.6338 0.0087
-6.500 0.1685 0.02215 0.01656 -0.1731 0.6317 0.0088
-6.250 0.1912 0.02013 0.01410 -0.1737 0.6305 0.0090
-6.000 0.2164 0.01889 0.01254 -0.1740 0.6292 0.0092
-5.750 0.2428 0.01800 0.01141 -0.1743 0.6282 0.0094
-5.500 0.2687 0.01693 0.01022 -0.1747 0.6272 0.0097
-5.250 0.2958 0.01637 0.00958 -0.1751 0.6261 0.0101
-5.000 0.3233 0.01584 0.00895 -0.1754 0.6249 0.0106
-4.750 0.3510 0.01529 0.00829 -0.1757 0.6236 0.0109
-4.500 0.3789 0.01476 0.00765 -0.1760 0.6223 0.0112
-4.250 0.4070 0.01429 0.00708 -0.1763 0.6209 0.0115
-4.000 0.4353 0.01390 0.00660 -0.1766 0.6197 0.0117
-3.750 0.4636 0.01349 0.00613 -0.1769 0.6186 0.0121
-3.500 0.4921 0.01312 0.00572 -0.1773 0.6175 0.0125
-3.250 0.5208 0.01285 0.00541 -0.1777 0.6164 0.0130
-3.000 0.5497 0.01264 0.00514 -0.1781 0.6152 0.0135
-2.750 0.5786 0.01247 0.00491 -0.1785 0.6139 0.0140
-2.500 0.6074 0.01231 0.00471 -0.1789 0.6127 0.0150
-2.250 0.6360 0.01215 0.00455 -0.1793 0.6115 0.0161
-2.000 0.6646 0.01203 0.00442 -0.1796 0.6103 0.0172
-1.750 0.6934 0.01191 0.00431 -0.1800 0.6091 0.0189
-1.500 0.7222 0.01179 0.00422 -0.1804 0.6078 0.0261
-1.250 0.7509 0.01168 0.00418 -0.1808 0.6065 0.0427
-1.000 0.7796 0.01162 0.00416 -0.1812 0.6052 0.0571
-0.750 0.8083 0.01157 0.00413 -0.1816 0.6038 0.0684
-0.500 0.8370 0.01151 0.00411 -0.1821 0.6025 0.0841
-0.250 0.8657 0.01146 0.00409 -0.1825 0.6011 0.1018
0.000 0.8947 0.01138 0.00409 -0.1830 0.5999 0.1339
0.250 0.9241 0.01125 0.00412 -0.1838 0.5987 0.2035
0.500 0.9544 0.01103 0.00420 -0.1848 0.5975 0.3322
0.750 0.9848 0.01074 0.00434 -0.1860 0.5963 0.4999
1.000 1.0149 0.01042 0.00451 -0.1869 0.5951 0.6807
1.250 1.0347 0.01024 0.00474 -0.1852 0.5936 0.8396
1.500 1.0565 0.01029 0.00484 -0.1839 0.5921 0.8835
1.750 1.0765 0.01033 0.00491 -0.1823 0.5904 0.9151
2.000 1.0932 0.01032 0.00494 -0.1799 0.5888 0.9424
2.250 1.1107 0.01027 0.00490 -0.1778 0.5872 0.9770
2.500 1.1414 0.01033 0.00492 -0.1787 0.5859 1.0000
2.750 1.1704 0.01043 0.00499 -0.1793 0.5846 1.0000
3.000 1.1994 0.01054 0.00506 -0.1799 0.5833 1.0000
3.250 1.2286 0.01067 0.00514 -0.1805 0.5820 1.0000
3.500 1.2562 0.01080 0.00529 -0.1809 0.5805 1.0000
3.750 1.2833 0.01093 0.00544 -0.1812 0.5788 1.0000
4.000 1.3104 0.01106 0.00559 -0.1815 0.5769 1.0000
4.250 1.3375 0.01120 0.00574 -0.1817 0.5751 1.0000
4.500 1.3645 0.01133 0.00589 -0.1820 0.5734 1.0000
4.750 1.3914 0.01146 0.00603 -0.1823 0.5718 1.0000
5.000 1.4183 0.01159 0.00616 -0.1825 0.5702 1.0000
5.250 1.4454 0.01172 0.00627 -0.1828 0.5686 1.0000
5.500 1.4727 0.01185 0.00640 -0.1831 0.5670 1.0000
5.750 1.4979 0.01203 0.00661 -0.1831 0.5652 1.0000
6.000 1.5221 0.01222 0.00686 -0.1829 0.5633 1.0000
6.250 1.5460 0.01240 0.00710 -0.1827 0.5612 1.0000
6.500 1.5695 0.01258 0.00732 -0.1824 0.5589 1.0000
6.750 1.5925 0.01273 0.00749 -0.1819 0.5562 1.0000
7.000 1.6158 0.01285 0.00763 -0.1815 0.5533 1.0000
7.250 1.6369 0.01302 0.00781 -0.1807 0.5504 1.0000
7.500 1.6528 0.01327 0.00815 -0.1790 0.5470 1.0000
7.750 1.6693 0.01353 0.00846 -0.1774 0.5432 1.0000
8.000 1.6864 0.01375 0.00870 -0.1759 0.5392 1.0000
8.250 1.7002 0.01407 0.00904 -0.1740 0.5338 1.0000
8.500 1.7117 0.01450 0.00953 -0.1718 0.5281 1.0000
8.750 1.7232 0.01495 0.00995 -0.1696 0.5216 1.0000
9.000 1.7305 0.01563 0.01072 -0.1670 0.5143 1.0000
9.250 1.7356 0.01645 0.01152 -0.1641 0.5056 1.0000
9.500 1.7374 0.01756 0.01267 -0.1611 0.4951 1.0000
9.750 1.7401 0.01878 0.01391 -0.1584 0.4857 1.0000
10.000 1.7400 0.02027 0.01539 -0.1556 0.4760 1.0000
10.250 1.7422 0.02178 0.01695 -0.1532 0.4663 1.0000
10.500 1.7408 0.02360 0.01877 -0.1506 0.4556 1.0000
10.750 1.7316 0.02602 0.02118 -0.1474 0.4403 1.0000
11.000 1.7203 0.02872 0.02385 -0.1441 0.4234 1.0000
11.250 1.7022 0.03205 0.02711 -0.1405 0.4026 1.0000
11.500 1.6828 0.03570 0.03068 -0.1370 0.3812 1.0000
11.750 1.6612 0.03973 0.03460 -0.1336 0.3576 1.0000
12.000 1.6439 0.04359 0.03837 -0.1308 0.3367 1.0000
12.250 1.6302 0.04730 0.04199 -0.1284 0.3149 1.0000
12.500 1.6179 0.05103 0.04563 -0.1264 0.2945 1.0000
12.750 1.6068 0.05475 0.04926 -0.1245 0.2741 1.0000
13.000 1.6009 0.05805 0.05250 -0.1231 0.2561 1.0000
13.250 1.5961 0.06133 0.05573 -0.1219 0.2392 1.0000
13.500 1.5927 0.06451 0.05885 -0.1208 0.2225 1.0000
13.750 1.5899 0.06771 0.06200 -0.1199 0.2069 1.0000
14.000 1.5879 0.07086 0.06510 -0.1191 0.1913 1.0000
14.250 1.5866 0.07401 0.06820 -0.1184 0.1766 1.0000
14.500 1.5854 0.07718 0.07132 -0.1178 0.1620 1.0000
14.750 1.5846 0.08034 0.07443 -0.1172 0.1471 1.0000
15.000 1.5839 0.08355 0.07760 -0.1168 0.1339 1.0000
15.250 1.5849 0.08657 0.08058 -0.1165 0.1215 1.0000
15.500 1.5857 0.08968 0.08367 -0.1162 0.1103 1.0000
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Polar data table (+)
Polar graphs
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