FX 73-CL2-152 (fx73cl2152-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 73-CL2-152 (fx73cl2152-il) Reynolds number: 200,000 Max Cl/Cd: 74.88 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx73cl2152-il-200000-n5.txt Download as CSV file: xf-fx73cl2152-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.1033 0.09271 0.08894 -0.0717 0.9332 0.0361
-8.500 -0.1217 0.07941 0.07564 -0.0788 0.9051 0.0369
-8.000 -0.2331 0.03131 0.02635 -0.1391 0.8610 0.0388
-7.750 -0.1804 0.02737 0.02191 -0.1495 0.8413 0.0399
-7.500 -0.1051 0.02364 0.01738 -0.1629 0.8132 0.0417
-7.250 -0.0161 0.02204 0.01545 -0.1761 0.7640 0.0433
-7.000 0.0442 0.02106 0.01394 -0.1837 0.7075 0.0449
-6.750 0.0779 0.02035 0.01279 -0.1856 0.6665 0.0460
-6.500 0.1071 0.01976 0.01181 -0.1865 0.6353 0.0470
-6.250 0.1341 0.01931 0.01121 -0.1867 0.6110 0.0481
-6.000 0.1617 0.01897 0.01072 -0.1870 0.5913 0.0494
-5.750 0.1902 0.01858 0.01017 -0.1874 0.5750 0.0509
-5.500 0.2194 0.01819 0.00958 -0.1879 0.5613 0.0525
-5.250 0.2486 0.01780 0.00905 -0.1884 0.5495 0.0538
-5.000 0.2783 0.01747 0.00866 -0.1890 0.5386 0.0554
-4.750 0.3081 0.01721 0.00829 -0.1896 0.5295 0.0575
-4.500 0.3384 0.01696 0.00791 -0.1901 0.5206 0.0599
-4.000 0.4001 0.01649 0.00730 -0.1916 0.5054 0.0652
-3.750 0.4314 0.01628 0.00701 -0.1924 0.4988 0.0686
-3.250 0.4943 0.01596 0.00657 -0.1939 0.4883 0.0788
-3.000 0.5260 0.01581 0.00638 -0.1947 0.4833 0.0865
-2.750 0.5576 0.01567 0.00624 -0.1955 0.4787 0.0997
-2.500 0.5889 0.01560 0.00616 -0.1963 0.4744 0.1219
-2.250 0.6199 0.01554 0.00615 -0.1969 0.4702 0.1488
-2.000 0.6502 0.01553 0.00617 -0.1973 0.4659 0.1713
-1.750 0.6800 0.01558 0.00620 -0.1976 0.4621 0.1898
-1.500 0.7097 0.01566 0.00623 -0.1979 0.4587 0.2056
-1.250 0.7393 0.01577 0.00628 -0.1981 0.4556 0.2207
-1.000 0.7690 0.01587 0.00634 -0.1983 0.4525 0.2359
-0.750 0.7986 0.01592 0.00644 -0.1986 0.4490 0.2541
-0.500 0.8281 0.01599 0.00654 -0.1988 0.4456 0.2735
-0.250 0.8576 0.01608 0.00664 -0.1990 0.4424 0.2889
0.000 0.8868 0.01619 0.00672 -0.1992 0.4394 0.3021
0.500 0.9455 0.01646 0.00696 -0.1995 0.4335 0.3341
0.750 0.9744 0.01655 0.00711 -0.1996 0.4304 0.3518
1.000 1.0031 0.01665 0.00726 -0.1997 0.4273 0.3721
1.250 1.0316 0.01678 0.00742 -0.1997 0.4244 0.3938
1.500 1.0601 0.01692 0.00759 -0.1997 0.4217 0.4163
1.750 1.0887 0.01710 0.00777 -0.1998 0.4190 0.4410
2.000 1.1178 0.01732 0.00799 -0.1999 0.4164 0.4668
2.250 1.1456 0.01745 0.00822 -0.1998 0.4137 0.4930
2.500 1.1734 0.01760 0.00846 -0.1997 0.4110 0.5207
2.750 1.2009 0.01776 0.00871 -0.1995 0.4082 0.5486
3.000 1.2282 0.01794 0.00894 -0.1992 0.4053 0.5765
3.250 1.2552 0.01812 0.00917 -0.1990 0.4026 0.6044
3.500 1.2824 0.01834 0.00941 -0.1987 0.4001 0.6339
3.750 1.3100 0.01860 0.00969 -0.1986 0.3979 0.6640
4.000 1.3357 0.01878 0.00999 -0.1980 0.3955 0.6951
4.250 1.3606 0.01895 0.01028 -0.1973 0.3929 0.7280
4.500 1.3843 0.01912 0.01056 -0.1963 0.3903 0.7634
4.750 1.4062 0.01926 0.01080 -0.1950 0.3877 0.8052
5.000 1.4219 0.01929 0.01094 -0.1922 0.3852 0.8722
5.250 1.4405 0.01937 0.01103 -0.1902 0.3828 1.0000
5.500 1.4678 0.01971 0.01130 -0.1902 0.3803 1.0000
5.750 1.4936 0.02002 0.01164 -0.1898 0.3777 1.0000
6.000 1.5187 0.02033 0.01200 -0.1893 0.3750 1.0000
6.250 1.5435 0.02064 0.01236 -0.1888 0.3721 1.0000
6.500 1.5682 0.02095 0.01270 -0.1883 0.3694 1.0000
6.750 1.5926 0.02127 0.01303 -0.1876 0.3669 1.0000
7.000 1.6171 0.02160 0.01334 -0.1871 0.3644 1.0000
7.250 1.6422 0.02198 0.01367 -0.1866 0.3619 1.0000
7.500 1.6637 0.02232 0.01414 -0.1855 0.3589 1.0000
7.750 1.6855 0.02269 0.01459 -0.1845 0.3557 1.0000
8.000 1.7072 0.02305 0.01502 -0.1834 0.3529 1.0000
8.250 1.7283 0.02341 0.01542 -0.1823 0.3502 1.0000
8.500 1.7495 0.02378 0.01580 -0.1811 0.3478 1.0000
8.750 1.7715 0.02418 0.01618 -0.1802 0.3455 1.0000
9.000 1.7894 0.02462 0.01674 -0.1785 0.3425 1.0000
9.250 1.8065 0.02507 0.01731 -0.1767 0.3392 1.0000
9.500 1.8239 0.02553 0.01786 -0.1750 0.3362 1.0000
9.750 1.8415 0.02599 0.01838 -0.1734 0.3335 1.0000
10.000 1.8594 0.02644 0.01886 -0.1718 0.3309 1.0000
10.250 1.8742 0.02692 0.01936 -0.1697 0.3272 1.0000
10.500 1.8834 0.02748 0.02009 -0.1668 0.3213 1.0000
10.750 1.8931 0.02799 0.02062 -0.1640 0.3155 1.0000
11.000 1.9033 0.02862 0.02129 -0.1614 0.3102 1.0000
11.250 1.9135 0.02938 0.02217 -0.1590 0.3046 1.0000
11.500 1.9236 0.03016 0.02301 -0.1566 0.3001 1.0000
11.750 1.9337 0.03100 0.02386 -0.1543 0.2964 1.0000
12.000 1.9432 0.03199 0.02502 -0.1521 0.2919 1.0000
12.250 1.9512 0.03306 0.02618 -0.1499 0.2873 1.0000
12.500 1.9580 0.03423 0.02740 -0.1476 0.2831 1.0000
12.750 1.9641 0.03552 0.02878 -0.1453 0.2790 1.0000
13.000 1.9689 0.03700 0.03039 -0.1432 0.2741 1.0000
13.250 1.9717 0.03864 0.03211 -0.1410 0.2694 1.0000
13.500 1.9733 0.04046 0.03397 -0.1390 0.2652 1.0000
13.750 1.9742 0.04253 0.03621 -0.1372 0.2602 1.0000
14.000 1.9724 0.04491 0.03869 -0.1354 0.2552 1.0000
14.250 1.9689 0.04755 0.04136 -0.1339 0.2505 1.0000
14.500 1.9647 0.05055 0.04454 -0.1327 0.2452 1.0000
14.750 1.9571 0.05406 0.04817 -0.1318 0.2396 1.0000
15.000 1.9477 0.05796 0.05214 -0.1312 0.2343 1.0000
15.250 1.9362 0.06244 0.05679 -0.1311 0.2280 1.0000
15.500 1.9210 0.06755 0.06198 -0.1313 0.2216 1.0000
15.750 1.9044 0.07318 0.06777 -0.1319 0.2150 1.0000
16.000 1.8840 0.07951 0.07420 -0.1330 0.2075 1.0000
16.250 1.8632 0.08615 0.08097 -0.1344 0.1996 1.0000
16.500 1.8404 0.09322 0.08810 -0.1361 0.1914 1.0000
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Polar data table (+)
Polar graphs
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