FX 73-CL2-152 (fx73cl2152-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 73-CL2-152 (fx73cl2152-il) Reynolds number: 50,000 Max Cl/Cd: 32.64 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx73cl2152-il-50000-n5.txt Download as CSV file: xf-fx73cl2152-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 73-CL2-152
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.1221 0.10425 0.09785 -0.0552 0.9515 0.0939
-7.250 -0.1046 0.10038 0.09399 -0.0577 0.9345 0.0917
-7.000 -0.0930 0.09638 0.09000 -0.0608 0.9152 0.0896
-6.750 -0.0842 0.09222 0.08586 -0.0643 0.8955 0.0881
-6.500 -0.0777 0.08883 0.08250 -0.0663 0.8717 0.0883
-6.250 -0.0692 0.08527 0.07894 -0.0686 0.8500 0.0890
-6.000 -0.0579 0.08111 0.07476 -0.0723 0.8297 0.0893
-5.750 -0.0431 0.07613 0.06972 -0.0776 0.8103 0.0889
-5.500 -0.0262 0.07038 0.06388 -0.0846 0.7917 0.0884
-5.250 -0.0042 0.06447 0.05783 -0.0930 0.7738 0.0892
-5.000 0.0231 0.05588 0.04899 -0.1072 0.7570 0.0914
-4.750 0.0894 0.03962 0.03146 -0.1396 0.7433 0.0945
-4.500 0.1392 0.03734 0.02890 -0.1457 0.7254 0.0988
-4.250 0.2020 0.03344 0.02414 -0.1562 0.7084 0.1053
-4.000 0.2458 0.03201 0.02241 -0.1602 0.6919 0.1104
-3.750 0.2904 0.03040 0.02025 -0.1647 0.6761 0.1186
-3.500 0.3265 0.02977 0.01952 -0.1666 0.6621 0.1250
-3.250 0.3678 0.02893 0.01833 -0.1696 0.6500 0.1357
-3.000 0.4036 0.02832 0.01748 -0.1716 0.6376 0.1483
-2.750 0.4401 0.02795 0.01695 -0.1735 0.6276 0.1644
-2.500 0.4742 0.02775 0.01672 -0.1749 0.6178 0.1843
-2.250 0.5115 0.02763 0.01648 -0.1769 0.6098 0.2106
-2.000 0.5444 0.02763 0.01640 -0.1781 0.6008 0.2386
-1.750 0.5797 0.02775 0.01645 -0.1795 0.5935 0.2668
-1.500 0.6123 0.02792 0.01652 -0.1806 0.5859 0.2962
-1.250 0.6429 0.02811 0.01672 -0.1811 0.5789 0.3202
-1.000 0.6773 0.02824 0.01674 -0.1822 0.5733 0.3430
-0.750 0.7070 0.02841 0.01687 -0.1827 0.5672 0.3627
-0.500 0.7366 0.02859 0.01699 -0.1831 0.5609 0.3818
-0.250 0.7684 0.02876 0.01706 -0.1837 0.5555 0.4022
0.000 0.8000 0.02897 0.01717 -0.1844 0.5507 0.4229
0.250 0.8253 0.02930 0.01758 -0.1840 0.5449 0.4435
0.500 0.8530 0.02961 0.01789 -0.1840 0.5398 0.4659
0.750 0.8826 0.02988 0.01812 -0.1842 0.5353 0.4918
1.000 0.9123 0.03021 0.01841 -0.1844 0.5310 0.5205
1.250 0.9330 0.03071 0.01906 -0.1833 0.5257 0.5467
1.750 0.9831 0.03150 0.01994 -0.1820 0.5166 0.6118
2.000 1.0105 0.03180 0.02022 -0.1816 0.5131 0.6493
2.250 1.0261 0.03243 0.02102 -0.1795 0.5083 0.6842
2.500 1.0419 0.03297 0.02172 -0.1773 0.5035 0.7233
2.750 1.0590 0.03335 0.02218 -0.1751 0.4994 0.7696
3.000 1.0734 0.03349 0.02239 -0.1722 0.4960 0.8273
3.250 1.0923 0.03347 0.02233 -0.1701 0.4930 1.0000
3.500 1.1098 0.03480 0.02373 -0.1696 0.4876 1.0000
3.750 1.1330 0.03586 0.02475 -0.1696 0.4827 1.0000
4.000 1.1609 0.03670 0.02548 -0.1701 0.4787 1.0000
4.250 1.1934 0.03733 0.02594 -0.1711 0.4753 1.0000
4.500 1.2133 0.03848 0.02709 -0.1704 0.4712 1.0000
4.750 1.2210 0.04014 0.02889 -0.1682 0.4660 1.0000
5.000 1.2382 0.04139 0.03015 -0.1672 0.4617 1.0000
5.250 1.2632 0.04226 0.03097 -0.1671 0.4581 1.0000
5.500 1.2954 0.04283 0.03143 -0.1678 0.4552 1.0000
5.750 1.2886 0.04527 0.03408 -0.1640 0.4499 1.0000
6.000 1.2830 0.04770 0.03667 -0.1605 0.4446 1.0000
6.250 1.2950 0.04926 0.03826 -0.1590 0.4407 1.0000
6.500 1.3198 0.05018 0.03915 -0.1588 0.4377 1.0000
6.750 1.3546 0.05061 0.03950 -0.1596 0.4354 1.0000
7.000 1.2165 0.06175 0.05122 -0.1463 0.4231 1.0000
7.250 1.2371 0.06289 0.05234 -0.1458 0.4198 1.0000
7.500 1.2685 0.06315 0.05257 -0.1458 0.4176 1.0000
8.000 1.1404 0.08450 0.07434 -0.1446 0.3961 1.0000
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Polar data table (+)
Polar graphs
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