EPPLER EA 6(-1)-009 AIRFOIL (ea61009-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER EA 6(-1)-009 AIRFOIL (ea61009-il) Reynolds number: 50,000 Max Cl/Cd: 23.64 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ea61009-il-50000.txt Download as CSV file: xf-ea61009-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER EA 6(-1)-009 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5759 0.09632 0.08910 0.0329 1.0000 0.4156
-8.000 -0.5742 0.09320 0.08601 0.0329 1.0000 0.4294
-7.750 -0.7377 0.06412 0.05689 -0.0097 1.0000 0.1825
-7.500 -0.7439 0.05684 0.04900 -0.0124 1.0000 0.1686
-7.250 -0.7322 0.05227 0.04416 -0.0127 1.0000 0.1672
-7.000 -0.7192 0.04801 0.03949 -0.0129 1.0000 0.1663
-6.750 -0.7032 0.04396 0.03499 -0.0129 1.0000 0.1641
-6.500 -0.6848 0.04033 0.03087 -0.0127 1.0000 0.1627
-6.250 -0.6642 0.03754 0.02761 -0.0124 1.0000 0.1656
-6.000 -0.6417 0.03498 0.02454 -0.0119 1.0000 0.1682
-5.750 -0.6170 0.03262 0.02171 -0.0114 1.0000 0.1695
-5.500 -0.5911 0.03038 0.01933 -0.0111 1.0000 0.1722
-5.250 -0.5653 0.02871 0.01758 -0.0106 1.0000 0.1788
-5.000 -0.5388 0.02717 0.01576 -0.0101 1.0000 0.1858
-4.750 -0.5114 0.02561 0.01427 -0.0096 1.0000 0.1927
-4.500 -0.4836 0.02426 0.01282 -0.0089 1.0000 0.2016
-4.250 -0.4568 0.02302 0.01162 -0.0081 1.0000 0.2156
-4.000 -0.4331 0.02165 0.01055 -0.0072 1.0000 0.2395
-3.750 -0.4132 0.01995 0.00940 -0.0059 1.0000 0.2880
-3.500 -0.4147 0.01754 0.00934 0.0011 1.0000 0.5923
-3.250 -0.4086 0.01830 0.01037 0.0096 1.0000 0.7457
-3.000 -0.3952 0.01900 0.01099 0.0161 1.0000 0.8101
-2.750 -0.3563 0.02001 0.01179 0.0198 1.0000 0.8807
-2.500 -0.1925 0.02065 0.01152 0.0004 1.0000 0.9528
-2.250 -0.0737 0.01923 0.00964 -0.0171 1.0000 1.0000
-2.000 -0.0569 0.01876 0.00910 -0.0168 1.0000 1.0000
-1.750 -0.0403 0.01836 0.00867 -0.0164 1.0000 1.0000
-1.500 -0.0244 0.01803 0.00832 -0.0158 1.0000 1.0000
-1.250 -0.0100 0.01777 0.00806 -0.0149 1.0000 1.0000
-1.000 0.0018 0.01757 0.00789 -0.0135 1.0000 1.0000
-0.750 0.0087 0.01747 0.00780 -0.0113 1.0000 1.0000
-0.500 0.0093 0.01743 0.00780 -0.0081 1.0000 1.0000
-0.250 0.0057 0.01744 0.00782 -0.0042 1.0000 1.0000
0.000 0.0000 0.01745 0.00783 0.0000 1.0000 1.0000
0.250 -0.0057 0.01744 0.00782 0.0042 1.0000 1.0000
0.500 -0.0092 0.01743 0.00780 0.0081 1.0000 1.0000
0.750 -0.0086 0.01746 0.00780 0.0113 1.0000 1.0000
1.000 -0.0017 0.01757 0.00789 0.0135 1.0000 1.0000
1.250 0.0100 0.01776 0.00806 0.0149 1.0000 1.0000
1.500 0.0245 0.01803 0.00832 0.0158 1.0000 1.0000
1.750 0.0404 0.01836 0.00867 0.0164 1.0000 1.0000
2.000 0.0570 0.01876 0.00911 0.0168 1.0000 1.0000
2.250 0.0738 0.01923 0.00963 0.0171 1.0000 1.0000
2.500 0.1930 0.02065 0.01151 -0.0004 0.9525 1.0000
2.750 0.3562 0.02001 0.01178 -0.0198 0.8806 1.0000
3.000 0.3952 0.01898 0.01097 -0.0161 0.8097 1.0000
3.250 0.4085 0.01830 0.01037 -0.0096 0.7456 1.0000
3.500 0.4146 0.01754 0.00934 -0.0010 0.5920 1.0000
3.750 0.4132 0.01995 0.00940 0.0059 0.2879 1.0000
4.000 0.4331 0.02166 0.01055 0.0072 0.2393 1.0000
4.250 0.4568 0.02302 0.01162 0.0081 0.2157 1.0000
4.500 0.4835 0.02426 0.01282 0.0089 0.2016 1.0000
4.750 0.5114 0.02561 0.01427 0.0096 0.1928 1.0000
5.000 0.5388 0.02717 0.01576 0.0101 0.1858 1.0000
5.250 0.5653 0.02871 0.01757 0.0106 0.1788 1.0000
5.500 0.5911 0.03038 0.01933 0.0111 0.1722 1.0000
5.750 0.6171 0.03262 0.02171 0.0114 0.1695 1.0000
6.000 0.6418 0.03498 0.02454 0.0119 0.1682 1.0000
6.250 0.6643 0.03753 0.02761 0.0123 0.1656 1.0000
6.500 0.6849 0.04034 0.03087 0.0127 0.1627 1.0000
6.750 0.7034 0.04397 0.03501 0.0129 0.1641 1.0000
7.000 0.7194 0.04803 0.03950 0.0129 0.1663 1.0000
7.250 0.7323 0.05229 0.04417 0.0127 0.1672 1.0000
7.500 0.7440 0.05686 0.04903 0.0124 0.1686 1.0000
7.750 0.7379 0.06417 0.05694 0.0096 0.1826 1.0000
8.000 0.5752 0.09323 0.08604 -0.0330 0.4293 1.0000
8.250 0.5767 0.09635 0.08913 -0.0329 0.4155 1.0000
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Polar data table (+)
Polar graphs
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