FX 73-CL2-152 (fx73cl2152-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 73-CL2-152 (fx73cl2152-il) Reynolds number: 100,000 Max Cl/Cd: 41.31 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx73cl2152-il-100000.txt Download as CSV file: xf-fx73cl2152-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1993 0.13423 0.12948 -0.0291 1.0000 0.1001
-9.750 -0.1993 0.13240 0.12771 -0.0287 1.0000 0.1034
-9.500 -0.2187 0.13276 0.12817 -0.0298 1.0000 0.1059
-9.000 -0.2078 0.12655 0.12211 -0.0272 1.0000 0.1086
-8.750 -0.2039 0.12457 0.12021 -0.0254 1.0000 0.1105
-8.500 -0.2065 0.12322 0.11896 -0.0238 1.0000 0.1125
-8.250 -0.1964 0.12081 0.11659 -0.0298 0.9957 0.1176
-8.000 -0.1797 0.11652 0.11232 -0.0389 0.9873 0.1199
-7.750 -0.1331 0.11090 0.10666 -0.0417 0.9810 0.1240
-7.500 0.0454 0.08905 0.08499 -0.0696 0.9133 0.1407
-7.250 0.0335 0.08717 0.08313 -0.0765 0.8953 0.1471
-7.000 0.0664 0.08053 0.07647 -0.0783 0.8786 0.1494
-6.750 0.1073 0.07545 0.07131 -0.0810 0.8558 0.1556
-6.500 0.0869 0.07411 0.06991 -0.0909 0.8307 0.1634
-6.250 0.0171 0.08591 0.08169 -0.0731 0.8884 0.1530
-6.000 0.0176 0.08401 0.07976 -0.0817 0.8607 0.1628
-5.750 0.0645 0.07774 0.07340 -0.0851 0.8395 0.1664
-5.500 0.1244 0.07260 0.06802 -0.0941 0.8120 0.1747
-5.250 0.1691 0.06712 0.06225 -0.1092 0.7795 0.1832
-5.000 0.1826 0.04299 0.03755 -0.1514 0.7675 0.1200
-4.750 0.2488 0.03253 0.02616 -0.1722 0.7416 0.1139
-4.500 0.3195 0.02698 0.01934 -0.1868 0.7173 0.1180
-4.250 0.3652 0.02510 0.01699 -0.1916 0.6974 0.1216
-4.000 0.4033 0.02435 0.01597 -0.1940 0.6807 0.1274
-3.750 0.4435 0.02333 0.01450 -0.1970 0.6667 0.1349
-3.500 0.4776 0.02287 0.01387 -0.1983 0.6542 0.1428
-3.250 0.5102 0.02246 0.01336 -0.1994 0.6434 0.1536
-3.000 0.5452 0.02212 0.01286 -0.2008 0.6342 0.1685
-2.750 0.5770 0.02201 0.01275 -0.2016 0.6258 0.1894
-2.500 0.6099 0.02191 0.01260 -0.2026 0.6175 0.2207
-2.250 0.6443 0.02210 0.01266 -0.2038 0.6105 0.2570
-2.000 0.6702 0.02225 0.01298 -0.2034 0.6030 0.2824
-1.750 0.6999 0.02250 0.01320 -0.2036 0.5967 0.3073
-1.500 0.7324 0.02284 0.01341 -0.2044 0.5916 0.3320
-1.250 0.7574 0.02308 0.01376 -0.2038 0.5855 0.3535
-1.000 0.7852 0.02331 0.01399 -0.2037 0.5795 0.3748
-0.750 0.8159 0.02350 0.01411 -0.2041 0.5745 0.3943
-0.500 0.8451 0.02375 0.01434 -0.2043 0.5699 0.4122
-0.250 0.8705 0.02395 0.01464 -0.2038 0.5646 0.4299
0.000 0.8982 0.02416 0.01486 -0.2037 0.5595 0.4497
0.250 0.9282 0.02440 0.01506 -0.2040 0.5550 0.4722
0.500 0.9581 0.02478 0.01540 -0.2043 0.5508 0.4980
0.750 0.9813 0.02511 0.01591 -0.2034 0.5460 0.5222
1.000 1.0060 0.02544 0.01636 -0.2027 0.5411 0.5497
1.250 1.0336 0.02577 0.01670 -0.2024 0.5368 0.5822
1.500 1.0629 0.02619 0.01710 -0.2024 0.5332 0.6182
1.750 1.0831 0.02670 0.01780 -0.2009 0.5292 0.6505
2.000 1.1027 0.02716 0.01844 -0.1992 0.5245 0.6851
2.250 1.1237 0.02755 0.01891 -0.1976 0.5202 0.7230
2.500 1.1456 0.02786 0.01926 -0.1961 0.5165 0.7646
2.750 1.1654 0.02821 0.01961 -0.1940 0.5134 0.8095
3.000 1.1718 0.02865 0.02027 -0.1898 0.5099 0.8597
3.250 1.1742 0.02884 0.02069 -0.1849 0.5057 1.0000
3.500 1.2118 0.02965 0.02140 -0.1877 0.5008 1.0000
3.750 1.2474 0.03030 0.02188 -0.1896 0.4967 1.0000
4.000 1.2828 0.03108 0.02247 -0.1912 0.4935 1.0000
4.250 1.2975 0.03240 0.02397 -0.1897 0.4891 1.0000
4.500 1.3154 0.03361 0.02526 -0.1886 0.4845 1.0000
4.750 1.3405 0.03444 0.02606 -0.1884 0.4803 1.0000
5.000 1.3710 0.03503 0.02655 -0.1890 0.4768 1.0000
5.250 1.4049 0.03578 0.02715 -0.1900 0.4736 1.0000
5.500 1.4016 0.03787 0.02957 -0.1860 0.4683 1.0000
5.750 1.4124 0.03948 0.03131 -0.1839 0.4638 1.0000
6.000 1.4346 0.04051 0.03235 -0.1833 0.4602 1.0000
6.250 1.4659 0.04109 0.03286 -0.1839 0.4573 1.0000
6.500 1.5003 0.04179 0.03343 -0.1849 0.4545 1.0000
6.750 1.4613 0.04607 0.03820 -0.1769 0.4480 1.0000
7.000 1.4538 0.04878 0.04107 -0.1730 0.4431 1.0000
7.250 1.4751 0.04987 0.04218 -0.1724 0.4399 1.0000
7.500 1.5152 0.04997 0.04220 -0.1738 0.4376 1.0000
7.750 1.5574 0.05027 0.04241 -0.1756 0.4355 1.0000
8.000 1.1836 0.08772 0.08082 -0.1553 0.4165 1.0000
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Polar data table (+)
Polar graphs
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