EPPLER 49 AIRFOIL (e49-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: EPPLER 49 AIRFOIL (e49-il) Reynolds number: 500,000 Max Cl/Cd: 119.1 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e49-il-500000.txt Download as CSV file: xf-e49-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.3898 0.18771 0.18536 -0.0336 0.9856 0.0060
-15.000 -0.3817 0.18528 0.18292 -0.0351 0.9853 0.0062
-8.750 -0.2880 0.11661 0.11444 -0.0429 0.9587 0.0084
-8.500 -0.2794 0.11344 0.11127 -0.0447 0.9547 0.0087
-8.250 -0.2665 0.11024 0.10807 -0.0478 0.9527 0.0092
-8.000 -0.2511 0.10722 0.10504 -0.0517 0.9514 0.0097
-7.750 -0.2611 0.10540 0.10325 -0.0486 0.9428 0.0103
-7.500 -0.2524 0.10299 0.10083 -0.0528 0.9337 0.0107
-5.750 -0.1210 0.07278 0.07054 -0.0857 0.9085 0.0114
-5.500 -0.0940 0.06881 0.06654 -0.0905 0.9070 0.0116
-5.250 -0.0627 0.06504 0.06273 -0.0960 0.9059 0.0121
-5.000 -0.0220 0.06075 0.05836 -0.1041 0.9052 0.0127
-4.750 0.0006 0.05751 0.05507 -0.1075 0.8994 0.0133
-4.500 0.0461 0.05313 0.05059 -0.1160 0.8977 0.0147
-4.250 0.1093 0.04932 0.04658 -0.1260 0.8968 0.0173
-4.000 0.1609 0.04519 0.04223 -0.1337 0.8962 0.0175
-3.750 0.2215 0.03748 0.03411 -0.1454 0.8969 0.0185
-3.500 0.2612 0.03479 0.03127 -0.1501 0.8962 0.0196
-1.250 0.5930 0.02241 0.01676 -0.1693 0.8842 0.0297
-1.000 0.6284 0.02152 0.01583 -0.1708 0.8831 0.0259
-0.750 0.6645 0.02080 0.01507 -0.1725 0.8821 0.0251
0.000 0.7854 0.01865 0.01278 -0.1798 0.8795 0.0350
0.500 0.8363 0.01661 0.01276 -0.1795 0.8699 1.0000
0.750 0.8716 0.01624 0.01235 -0.1811 0.8687 1.0000
1.000 0.9082 0.01581 0.01189 -0.1829 0.8676 1.0000
1.250 0.9456 0.01531 0.01137 -0.1849 0.8667 1.0000
1.500 0.9604 0.01528 0.01135 -0.1822 0.8571 1.0000
1.750 0.9989 0.01450 0.01057 -0.1842 0.8550 1.0000
2.250 1.0504 0.01373 0.00985 -0.1832 0.8419 1.0000
2.500 1.0683 0.01371 0.00985 -0.1812 0.8304 1.0000
3.250 1.1587 0.01249 0.00871 -0.1825 0.7925 1.0000
3.500 1.2422 0.01043 0.00616 -0.1936 0.7121 1.0000
3.750 1.2584 0.01101 0.00642 -0.1913 0.6592 1.0000
4.000 1.2568 0.01208 0.00709 -0.1853 0.5836 1.0000
4.250 1.2508 0.01351 0.00799 -0.1788 0.4861 1.0000
4.500 1.2507 0.01499 0.00888 -0.1738 0.3838 1.0000
4.750 1.2581 0.01632 0.00966 -0.1705 0.2900 1.0000
5.000 1.2648 0.01793 0.01056 -0.1673 0.1753 1.0000
5.250 1.2669 0.02015 0.01191 -0.1633 0.0360 1.0000
5.500 1.2828 0.02113 0.01276 -0.1614 0.0113 1.0000
5.750 1.3019 0.02176 0.01351 -0.1600 0.0101 1.0000
6.000 1.3203 0.02244 0.01431 -0.1585 0.0099 1.0000
6.250 1.3375 0.02322 0.01523 -0.1568 0.0094 1.0000
6.500 1.3539 0.02407 0.01618 -0.1551 0.0087 1.0000
6.750 1.3689 0.02505 0.01726 -0.1532 0.0083 1.0000
7.000 1.3823 0.02617 0.01850 -0.1509 0.0080 1.0000
7.250 1.3939 0.02746 0.01990 -0.1484 0.0076 1.0000
7.500 1.4034 0.02894 0.02149 -0.1456 0.0074 1.0000
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Polar data table (+)
Polar graphs
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