FX 73-CL2-152 (fx73cl2152-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 73-CL2-152 (fx73cl2152-il) Reynolds number: 200,000 Max Cl/Cd: 66.32 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx73cl2152-il-200000.txt Download as CSV file: xf-fx73cl2152-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.0407 0.09377 0.09044 -0.0687 0.9562 0.0804
-7.500 -0.0557 0.08836 0.08507 -0.0795 0.9412 0.0851
-7.250 -0.0258 0.08529 0.08200 -0.0783 0.9285 0.0860
-7.000 -0.0025 0.08266 0.07938 -0.0782 0.9097 0.0875
-6.750 0.0170 0.07967 0.07637 -0.0803 0.8823 0.0910
-6.500 -0.0562 0.03738 0.03313 -0.1410 0.8630 0.0672
-6.250 0.0013 0.02991 0.02512 -0.1543 0.8414 0.0664
-6.000 0.1025 0.02365 0.01789 -0.1743 0.8036 0.0687
-5.750 0.1991 0.02127 0.01474 -0.1894 0.7339 0.0712
-5.500 0.2398 0.02030 0.01312 -0.1927 0.6847 0.0731
-5.250 0.2732 0.01975 0.01198 -0.1942 0.6528 0.0753
-5.000 0.3025 0.01891 0.01093 -0.1949 0.6304 0.0775
-4.750 0.3320 0.01847 0.01030 -0.1954 0.6125 0.0797
-4.500 0.3620 0.01804 0.00967 -0.1958 0.5975 0.0824
-4.250 0.3931 0.01760 0.00902 -0.1965 0.5856 0.0858
-4.000 0.4235 0.01726 0.00866 -0.1971 0.5753 0.0899
-3.750 0.4551 0.01702 0.00825 -0.1978 0.5666 0.0944
-3.500 0.4866 0.01664 0.00790 -0.1987 0.5585 0.1002
-3.250 0.5204 0.01649 0.00762 -0.1999 0.5517 0.1090
-3.000 0.5519 0.01624 0.00742 -0.2006 0.5448 0.1209
-2.750 0.5846 0.01606 0.00729 -0.2017 0.5383 0.1429
-2.500 0.6194 0.01610 0.00730 -0.2031 0.5327 0.1827
-2.250 0.6499 0.01619 0.00743 -0.2036 0.5276 0.2124
-2.000 0.6801 0.01633 0.00753 -0.2039 0.5226 0.2340
-1.750 0.7106 0.01646 0.00762 -0.2044 0.5180 0.2521
-1.500 0.7425 0.01667 0.00775 -0.2051 0.5136 0.2687
-1.250 0.7721 0.01677 0.00787 -0.2053 0.5093 0.2845
-1.000 0.8015 0.01687 0.00798 -0.2055 0.5051 0.3008
-0.750 0.8313 0.01701 0.00812 -0.2058 0.5011 0.3199
-0.500 0.8615 0.01718 0.00825 -0.2061 0.4972 0.3393
-0.250 0.8937 0.01746 0.00844 -0.2069 0.4934 0.3573
0.000 0.9220 0.01751 0.00861 -0.2069 0.4898 0.3744
0.250 0.9508 0.01759 0.00876 -0.2069 0.4859 0.3940
0.500 0.9802 0.01771 0.00892 -0.2071 0.4822 0.4167
0.750 1.0102 0.01785 0.00909 -0.2074 0.4788 0.4417
1.000 1.0408 0.01808 0.00934 -0.2079 0.4756 0.4698
1.250 1.0708 0.01838 0.00968 -0.2082 0.4723 0.5009
1.500 1.0974 0.01851 0.00996 -0.2078 0.4689 0.5307
1.750 1.1251 0.01869 0.01024 -0.2076 0.4654 0.5632
2.000 1.1532 0.01890 0.01051 -0.2075 0.4621 0.5959
2.250 1.1813 0.01911 0.01076 -0.2074 0.4590 0.6274
2.500 1.2106 0.01942 0.01107 -0.2075 0.4559 0.6609
2.750 1.2376 0.01977 0.01149 -0.2072 0.4528 0.6944
3.000 1.2613 0.01995 0.01184 -0.2061 0.4497 0.7263
3.250 1.2855 0.02016 0.01216 -0.2052 0.4465 0.7610
3.500 1.3088 0.02034 0.01243 -0.2040 0.4434 0.7994
3.750 1.3290 0.02046 0.01263 -0.2022 0.4406 0.8452
4.000 1.3391 0.02034 0.01259 -0.1981 0.4383 1.0000
4.250 1.3740 0.02101 0.01310 -0.1998 0.4351 1.0000
4.500 1.3998 0.02131 0.01348 -0.1995 0.4319 1.0000
4.750 1.4258 0.02166 0.01387 -0.1992 0.4282 1.0000
5.000 1.4529 0.02201 0.01421 -0.1992 0.4248 1.0000
5.250 1.4812 0.02237 0.01454 -0.1993 0.4218 1.0000
5.500 1.5108 0.02278 0.01486 -0.1997 0.4190 1.0000
5.750 1.5410 0.02347 0.01547 -0.2003 0.4161 1.0000
6.000 1.5627 0.02386 0.01600 -0.1992 0.4130 1.0000
6.250 1.5855 0.02428 0.01651 -0.1983 0.4094 1.0000
6.500 1.6099 0.02466 0.01692 -0.1977 0.4059 1.0000
6.750 1.6365 0.02499 0.01723 -0.1975 0.4028 1.0000
7.000 1.6653 0.02540 0.01757 -0.1977 0.4001 1.0000
7.250 1.6932 0.02611 0.01826 -0.1979 0.3972 1.0000
7.500 1.7116 0.02662 0.01894 -0.1963 0.3940 1.0000
7.750 1.7320 0.02715 0.01959 -0.1950 0.3905 1.0000
8.000 1.7545 0.02758 0.02008 -0.1941 0.3872 1.0000
8.250 1.7800 0.02792 0.02041 -0.1938 0.3843 1.0000
8.500 1.8086 0.02830 0.02075 -0.1940 0.3816 1.0000
8.750 1.8342 0.02905 0.02151 -0.1938 0.3789 1.0000
9.000 1.8483 0.02973 0.02241 -0.1915 0.3756 1.0000
9.250 1.8653 0.03036 0.02318 -0.1898 0.3722 1.0000
9.500 1.8857 0.03080 0.02369 -0.1886 0.3690 1.0000
9.750 1.9112 0.03094 0.02380 -0.1882 0.3658 1.0000
10.000 1.9419 0.03095 0.02368 -0.1887 0.3616 1.0000
10.250 1.9443 0.03135 0.02433 -0.1843 0.3564 1.0000
10.500 1.9588 0.03133 0.02436 -0.1819 0.3514 1.0000
10.750 1.9830 0.03126 0.02423 -0.1811 0.3477 1.0000
11.000 2.0070 0.03161 0.02456 -0.1806 0.3444 1.0000
11.250 2.0069 0.03238 0.02559 -0.1761 0.3405 1.0000
11.500 2.0129 0.03291 0.02625 -0.1725 0.3368 1.0000
11.750 2.0265 0.03317 0.02654 -0.1702 0.3332 1.0000
12.000 2.0485 0.03327 0.02660 -0.1692 0.3299 1.0000
12.250 2.0531 0.03406 0.02752 -0.1657 0.3264 1.0000
12.500 2.0490 0.03510 0.02877 -0.1610 0.3225 1.0000
12.750 2.0547 0.03579 0.02956 -0.1579 0.3186 1.0000
13.000 2.0688 0.03613 0.02990 -0.1560 0.3149 1.0000
13.250 2.0793 0.03685 0.03066 -0.1538 0.3111 1.0000
13.500 2.0690 0.03855 0.03261 -0.1492 0.3069 1.0000
13.750 2.0694 0.03978 0.03395 -0.1462 0.3026 1.0000
14.000 2.0806 0.04043 0.03460 -0.1443 0.2984 1.0000
14.250 2.0780 0.04213 0.03643 -0.1415 0.2941 1.0000
14.500 2.0661 0.04457 0.03907 -0.1382 0.2892 1.0000
14.750 2.0665 0.04622 0.04079 -0.1361 0.2843 1.0000
15.000 2.0693 0.04790 0.04250 -0.1344 0.2794 1.0000
15.250 2.0490 0.05178 0.04661 -0.1320 0.2741 1.0000
15.500 2.0453 0.05432 0.04921 -0.1307 0.2685 1.0000
15.750 2.0366 0.05764 0.05262 -0.1296 0.2628 1.0000
16.000 2.0128 0.06300 0.05818 -0.1290 0.2564 1.0000
16.250 2.0148 0.06540 0.06053 -0.1285 0.2496 1.0000
16.500 1.9770 0.07340 0.06881 -0.1293 0.2424 1.0000
16.750 1.9725 0.07695 0.07231 -0.1294 0.2345 1.0000
17.000 1.9314 0.08632 0.08193 -0.1316 0.2257 1.0000
17.250 1.9099 0.09292 0.08859 -0.1332 0.2162 1.0000
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Polar data table (+)
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