FX 73-CL2-152 (fx73cl2152-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 73-CL2-152 (fx73cl2152-il) Reynolds number: 100,000 Max Cl/Cd: 52.83 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx73cl2152-il-100000-n5.txt Download as CSV file: xf-fx73cl2152-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.0930 0.09821 0.09328 -0.0639 0.9439 0.0574
-8.000 -0.0858 0.09444 0.08953 -0.0661 0.9287 0.0568
-7.500 -0.0788 0.08646 0.08158 -0.0700 0.8894 0.0555
-7.250 -0.0736 0.08189 0.07701 -0.0732 0.8677 0.0551
-7.000 -0.0599 0.07752 0.07258 -0.0774 0.8453 0.0559
-6.750 -0.0470 0.07242 0.06740 -0.0831 0.8202 0.0569
-6.500 -0.0358 0.06561 0.06047 -0.0912 0.7936 0.0574
-6.250 -0.0385 0.03286 0.02630 -0.1441 0.7774 0.0580
-6.000 0.0310 0.02869 0.02131 -0.1568 0.7478 0.0610
-5.750 0.0873 0.02684 0.01899 -0.1638 0.7143 0.0633
-5.500 0.1392 0.02511 0.01667 -0.1699 0.6839 0.0656
-5.250 0.1813 0.02404 0.01519 -0.1735 0.6578 0.0684
-5.000 0.2184 0.02341 0.01434 -0.1759 0.6360 0.0711
-4.750 0.2554 0.02266 0.01327 -0.1781 0.6178 0.0740
-4.500 0.2904 0.02204 0.01245 -0.1798 0.6027 0.0768
-4.250 0.3252 0.02163 0.01190 -0.1814 0.5902 0.0809
-4.000 0.3590 0.02118 0.01127 -0.1828 0.5789 0.0855
-3.750 0.3932 0.02083 0.01083 -0.1843 0.5695 0.0903
-3.500 0.4265 0.02050 0.01041 -0.1856 0.5601 0.0971
-3.000 0.4935 0.02002 0.00976 -0.1881 0.5442 0.1189
-2.750 0.5269 0.01985 0.00961 -0.1894 0.5370 0.1371
-2.500 0.5604 0.01982 0.00947 -0.1906 0.5313 0.1626
-2.250 0.5921 0.01981 0.00950 -0.1914 0.5252 0.1871
-2.000 0.6235 0.01989 0.00951 -0.1921 0.5197 0.2101
-1.750 0.6548 0.02001 0.00953 -0.1928 0.5148 0.2313
-1.500 0.6855 0.02015 0.00959 -0.1933 0.5100 0.2516
-1.250 0.7152 0.02027 0.00971 -0.1936 0.5047 0.2728
-1.000 0.7451 0.02040 0.00982 -0.1940 0.5000 0.2932
-0.750 0.7754 0.02054 0.00991 -0.1944 0.4961 0.3100
-0.500 0.8062 0.02069 0.00999 -0.1949 0.4926 0.3252
-0.250 0.8350 0.02080 0.01013 -0.1950 0.4882 0.3412
0.000 0.8641 0.02095 0.01026 -0.1951 0.4838 0.3585
0.250 0.8934 0.02110 0.01042 -0.1953 0.4799 0.3769
0.500 0.9232 0.02128 0.01057 -0.1956 0.4764 0.3969
0.750 0.9536 0.02152 0.01075 -0.1960 0.4733 0.4194
1.000 0.9811 0.02170 0.01105 -0.1959 0.4693 0.4425
1.250 1.0088 0.02191 0.01134 -0.1957 0.4653 0.4675
1.500 1.0368 0.02214 0.01159 -0.1956 0.4616 0.4953
1.750 1.0649 0.02238 0.01184 -0.1956 0.4582 0.5242
2.000 1.0935 0.02265 0.01209 -0.1955 0.4553 0.5549
2.250 1.1197 0.02294 0.01246 -0.1951 0.4520 0.5853
2.500 1.1450 0.02322 0.01285 -0.1945 0.4484 0.6170
2.750 1.1698 0.02349 0.01322 -0.1938 0.4449 0.6493
3.000 1.1947 0.02375 0.01353 -0.1930 0.4416 0.6828
3.250 1.2195 0.02400 0.01381 -0.1922 0.4386 0.7190
3.500 1.2439 0.02425 0.01406 -0.1913 0.4360 0.7583
3.750 1.2629 0.02449 0.01444 -0.1894 0.4331 0.8028
4.000 1.2751 0.02461 0.01476 -0.1860 0.4299 0.8689
4.250 1.2949 0.02482 0.01503 -0.1844 0.4265 1.0000
4.500 1.3228 0.02526 0.01542 -0.1846 0.4231 1.0000
4.750 1.3514 0.02569 0.01576 -0.1848 0.4200 1.0000
5.000 1.3809 0.02614 0.01612 -0.1852 0.4175 1.0000
5.250 1.4065 0.02669 0.01669 -0.1850 0.4147 1.0000
5.500 1.4286 0.02730 0.01739 -0.1842 0.4113 1.0000
5.750 1.4518 0.02786 0.01803 -0.1835 0.4078 1.0000
6.000 1.4762 0.02837 0.01854 -0.1830 0.4046 1.0000
6.250 1.5022 0.02883 0.01897 -0.1828 0.4016 1.0000
6.500 1.5299 0.02927 0.01936 -0.1828 0.3990 1.0000
6.750 1.5523 0.02991 0.02005 -0.1821 0.3961 1.0000
7.000 1.5695 0.03068 0.02099 -0.1805 0.3926 1.0000
7.250 1.5888 0.03139 0.02182 -0.1792 0.3893 1.0000
7.500 1.6101 0.03202 0.02250 -0.1783 0.3863 1.0000
7.750 1.6336 0.03254 0.02303 -0.1777 0.3835 1.0000
8.000 1.6599 0.03299 0.02346 -0.1775 0.3811 1.0000
8.250 1.6791 0.03372 0.02427 -0.1763 0.3781 1.0000
8.500 1.6882 0.03477 0.02555 -0.1736 0.3743 1.0000
8.750 1.7017 0.03569 0.02660 -0.1715 0.3711 1.0000
9.000 1.7182 0.03646 0.02748 -0.1699 0.3682 1.0000
9.250 1.7388 0.03706 0.02812 -0.1689 0.3656 1.0000
9.500 1.7640 0.03749 0.02854 -0.1686 0.3633 1.0000
9.750 1.7737 0.03851 0.02969 -0.1661 0.3603 1.0000
10.000 1.7656 0.04010 0.03155 -0.1611 0.3565 1.0000
10.250 1.7665 0.04148 0.03310 -0.1576 0.3533 1.0000
10.500 1.7745 0.04256 0.03429 -0.1550 0.3505 1.0000
10.750 1.7917 0.04321 0.03499 -0.1537 0.3479 1.0000
11.000 1.8185 0.04347 0.03525 -0.1536 0.3457 1.0000
11.250 1.7934 0.04631 0.03837 -0.1476 0.3419 1.0000
11.500 1.7599 0.05007 0.04242 -0.1419 0.3373 1.0000
11.750 1.7589 0.05180 0.04426 -0.1395 0.3333 1.0000
12.000 1.8023 0.05006 0.04240 -0.1401 0.3296 1.0000
12.250 1.7302 0.05799 0.05073 -0.1343 0.3242 1.0000
12.500 1.6175 0.07343 0.06651 -0.1333 0.3152 1.0000
12.750 1.7075 0.06476 0.05772 -0.1317 0.3142 1.0000
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Polar data table (+)
Polar graphs
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