EPPLER 49 AIRFOIL (e49-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 49 AIRFOIL (e49-il) Reynolds number: 1,000,000 Max Cl/Cd: 155.5 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e49-il-1000000.txt Download as CSV file: xf-e49-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 49 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.0807 0.09201 0.09023 -0.1012 0.9286 0.0069
-8.250 -0.0728 0.08939 0.08761 -0.1033 0.9281 0.0069
-8.000 -0.1184 0.09088 0.08916 -0.0895 0.9192 0.0069
-7.750 -0.1033 0.08710 0.08538 -0.0937 0.9181 0.0069
-7.500 -0.0837 0.08315 0.08142 -0.0985 0.9174 0.0069
-7.250 -0.0601 0.07879 0.07705 -0.1043 0.9168 0.0069
-7.000 -0.0908 0.07683 0.07513 -0.0966 0.9081 0.0071
-6.750 -0.0746 0.07383 0.07213 -0.0985 0.9072 0.0074
-6.500 -0.0512 0.07035 0.06863 -0.1033 0.9064 0.0076
-6.250 -0.0244 0.06658 0.06484 -0.1093 0.9057 0.0079
-6.000 0.0071 0.06251 0.06073 -0.1163 0.9052 0.0082
-5.750 0.0043 0.06064 0.05886 -0.1141 0.8976 0.0087
-5.500 0.0387 0.05642 0.05460 -0.1212 0.8963 0.0091
-5.250 0.0887 0.05187 0.04996 -0.1313 0.8956 0.0106
-4.250 0.2912 0.02974 0.02702 -0.1676 0.8953 0.0116
-4.000 0.3290 0.02758 0.02469 -0.1714 0.8951 0.0121
-3.750 0.3670 0.02566 0.02257 -0.1748 0.8949 0.0128
-3.500 0.4052 0.02386 0.02055 -0.1777 0.8947 0.0138
-3.250 0.4422 0.02250 0.01898 -0.1799 0.8945 0.0156
-3.000 0.4754 0.02250 0.01888 -0.1806 0.8940 0.0174
-2.500 0.5531 0.01816 0.01385 -0.1863 0.8940 0.0203
-2.250 0.5868 0.01749 0.01313 -0.1878 0.8936 0.0226
-2.000 0.6207 0.01696 0.01252 -0.1892 0.8933 0.0257
-1.750 0.6542 0.01716 0.01268 -0.1903 0.8928 0.0285
-1.500 0.6692 0.01640 0.01185 -0.1877 0.8874 0.0281
-1.250 0.7066 0.01495 0.01027 -0.1894 0.8864 0.0170
-1.000 0.7459 0.01397 0.00926 -0.1917 0.8850 0.0172
-0.750 0.7842 0.01311 0.00833 -0.1939 0.8839 0.0196
-0.500 0.8186 0.01266 0.00785 -0.1954 0.8831 0.0216
-0.250 0.8527 0.01225 0.00744 -0.1968 0.8824 0.0241
0.000 0.8881 0.01152 0.00717 -0.1987 0.8818 0.2631
0.250 0.9201 0.01006 0.00723 -0.2002 0.8814 1.0000
0.500 0.9556 0.00958 0.00673 -0.2019 0.8807 1.0000
0.750 0.9714 0.00960 0.00674 -0.1993 0.8735 1.0000
1.000 1.0022 0.00915 0.00627 -0.2000 0.8696 1.0000
1.250 1.0371 0.00869 0.00580 -0.2016 0.8671 1.0000
1.500 1.0479 0.00902 0.00615 -0.1981 0.8567 1.0000
1.750 1.0725 0.00895 0.00608 -0.1975 0.8483 1.0000
2.000 1.1066 0.00857 0.00569 -0.1990 0.8394 1.0000
2.250 1.1443 0.00809 0.00515 -0.2012 0.8187 1.0000
2.500 1.1880 0.00764 0.00427 -0.2046 0.7411 1.0000
3.000 1.1938 0.00923 0.00527 -0.1943 0.6354 1.0000
3.250 1.1990 0.01004 0.00580 -0.1898 0.5767 1.0000
3.500 1.2027 0.01109 0.00640 -0.1853 0.4910 1.0000
3.750 1.2106 0.01219 0.00699 -0.1817 0.3948 1.0000
4.000 1.2218 0.01328 0.00755 -0.1790 0.3002 1.0000
4.250 1.2345 0.01434 0.00813 -0.1767 0.2123 1.0000
4.500 1.2421 0.01595 0.00903 -0.1735 0.0885 1.0000
4.750 1.2529 0.01740 0.01004 -0.1706 0.0077 1.0000
5.000 1.2736 0.01784 0.01054 -0.1695 0.0066 1.0000
5.250 1.2936 0.01834 0.01113 -0.1683 0.0063 1.0000
5.500 1.3127 0.01895 0.01182 -0.1669 0.0059 1.0000
5.750 1.3324 0.01946 0.01237 -0.1658 0.0056 1.0000
6.000 1.3510 0.02011 0.01310 -0.1644 0.0054 1.0000
6.250 1.3689 0.02082 0.01389 -0.1628 0.0051 1.0000
6.500 1.3858 0.02163 0.01478 -0.1611 0.0050 1.0000
6.750 1.4017 0.02250 0.01572 -0.1593 0.0046 1.0000
7.000 1.4155 0.02353 0.01684 -0.1571 0.0043 1.0000
7.250 1.4273 0.02474 0.01814 -0.1546 0.0041 1.0000
7.500 1.4375 0.02615 0.01966 -0.1518 0.0041 1.0000
7.750 1.4463 0.02789 0.02157 -0.1486 0.0043 1.0000
9.000 1.5164 0.04167 0.03684 -0.1384 0.0060 1.0000
9.250 1.5100 0.04496 0.04035 -0.1337 0.0060 1.0000
9.500 1.4997 0.04851 0.04412 -0.1286 0.0059 1.0000
9.750 1.4856 0.05223 0.04806 -0.1233 0.0059 1.0000
10.000 1.4691 0.05624 0.05229 -0.1182 0.0059 1.0000
10.250 1.4489 0.06043 0.05669 -0.1131 0.0059 1.0000
10.500 1.4234 0.06478 0.06126 -0.1080 0.0059 1.0000
10.750 1.3825 0.06909 0.06582 -0.1022 0.0059 1.0000
11.000 1.3543 0.07299 0.06992 -0.0986 0.0059 1.0000
11.250 1.3275 0.07776 0.07490 -0.0962 0.0059 1.0000
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Polar data table (+)
Polar graphs
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