EPPLER 339 AIRFOIL (e339-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 339 AIRFOIL (e339-il) Reynolds number: 50,000 Max Cl/Cd: 15.65 at α=-0.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e339-il-50000.txt Download as CSV file: xf-e339-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 339 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2921 0.10682 0.10080 -0.0279 1.0000 0.2015
-8.500 -0.2803 0.10271 0.09677 -0.0268 1.0000 0.2093
-8.250 -0.2920 0.10118 0.09540 -0.0270 1.0000 0.2194
-8.000 -0.2795 0.09733 0.09164 -0.0254 1.0000 0.2298
-7.750 -0.3056 0.09662 0.09115 -0.0254 1.0000 0.2382
-7.500 -0.2905 0.09290 0.08754 -0.0231 1.0000 0.2530
-7.250 -0.2933 0.09039 0.08521 -0.0211 1.0000 0.2653
-7.000 -0.3215 0.09002 0.08513 -0.0181 1.0000 0.2725
-6.750 -0.3589 0.09079 0.08617 -0.0120 1.0000 0.2715
-6.500 -0.3973 0.09190 0.08749 -0.0061 1.0000 0.2669
-6.250 -0.4325 0.09176 0.08743 -0.0090 0.9904 0.2749
-5.750 -0.3366 0.08252 0.07825 -0.0102 0.9680 0.3759
-5.500 -0.2362 0.07834 0.07402 -0.0045 0.9644 0.5325
-5.250 -0.0584 0.07021 0.06572 -0.0084 0.9657 0.7861
-4.750 0.0075 0.06166 0.05710 -0.0240 0.9344 0.7794
-4.500 -0.0759 0.06078 0.05633 -0.0259 0.9083 0.6391
-4.250 -0.1366 0.05798 0.05360 -0.0287 0.8856 0.5681
-4.000 -0.1839 0.05492 0.05044 -0.0336 0.8642 0.5068
-3.750 -0.1581 0.04941 0.04279 -0.0571 0.8452 0.2374
-3.500 -0.1119 0.04591 0.03825 -0.0591 0.8339 0.1625
-3.250 -0.0856 0.04385 0.03564 -0.0582 0.8214 0.1408
-3.000 -0.0369 0.04102 0.03209 -0.0599 0.8132 0.1243
-2.750 -0.0188 0.04025 0.03082 -0.0577 0.7998 0.1180
-2.500 0.0107 0.03902 0.02918 -0.0572 0.7891 0.1175
-2.250 0.0487 0.03723 0.02720 -0.0580 0.7795 0.1207
-2.000 0.3678 0.02670 0.01876 -0.0974 0.7719 1.0000
-1.750 0.3890 0.02707 0.01868 -0.0962 0.7605 1.0000
-1.500 0.4032 0.02781 0.01915 -0.0945 0.7486 1.0000
-1.250 0.4254 0.02818 0.01917 -0.0935 0.7396 1.0000
-1.000 0.4371 0.02911 0.01994 -0.0917 0.7285 1.0000
-0.750 0.4565 0.02968 0.02026 -0.0904 0.7201 1.0000
-0.500 0.4674 0.03072 0.02116 -0.0886 0.7102 1.0000
-0.250 0.4890 0.03124 0.02145 -0.0875 0.7032 1.0000
0.000 0.4922 0.03277 0.02294 -0.0851 0.6938 1.0000
0.250 0.5153 0.03323 0.02319 -0.0841 0.6873 1.0000
0.500 0.5118 0.03518 0.02514 -0.0811 0.6787 1.0000
0.750 0.5260 0.03617 0.02600 -0.0795 0.6719 1.0000
1.000 0.5350 0.03753 0.02726 -0.0774 0.6658 1.0000
1.250 0.5201 0.04002 0.02976 -0.0732 0.6584 1.0000
1.500 0.5394 0.04083 0.03045 -0.0720 0.6527 1.0000
1.750 0.5272 0.04324 0.03283 -0.0681 0.6472 1.0000
2.000 0.4868 0.04666 0.03629 -0.0615 0.6425 1.0000
2.250 0.4689 0.04891 0.03850 -0.0567 0.6382 1.0000
2.500 0.5288 0.04862 0.03802 -0.0598 0.6324 1.0000
2.750 0.4662 0.05249 0.04192 -0.0508 0.6312 1.0000
3.000 0.4342 0.05522 0.04462 -0.0453 0.6306 1.0000
3.250 0.4166 0.05758 0.04694 -0.0416 0.6304 1.0000
3.500 0.4101 0.05979 0.04910 -0.0391 0.6310 1.0000
3.750 0.4130 0.06200 0.05125 -0.0378 0.6327 1.0000
4.000 0.2263 0.06801 0.05769 -0.0274 0.7987 1.0000
4.250 0.2367 0.06948 0.05906 -0.0265 0.7880 1.0000
4.500 0.2684 0.07235 0.06179 -0.0285 0.7777 1.0000
4.750 0.2722 0.07305 0.06241 -0.0264 0.7635 1.0000
5.000 0.2850 0.07485 0.06413 -0.0259 0.7531 1.0000
5.250 0.3123 0.07742 0.06662 -0.0272 0.7422 1.0000
5.500 0.3145 0.07831 0.06746 -0.0253 0.7294 1.0000
5.750 0.3425 0.08150 0.07056 -0.0268 0.7213 1.0000
6.000 0.3510 0.08255 0.07158 -0.0256 0.7074 1.0000
6.250 0.3559 0.08401 0.07300 -0.0244 0.6965 1.0000
6.500 0.3895 0.08747 0.07641 -0.0264 0.6872 1.0000
6.750 0.3860 0.08801 0.07694 -0.0242 0.6740 1.0000
7.000 0.4112 0.09139 0.08028 -0.0254 0.6671 1.0000
7.250 0.4172 0.09248 0.08136 -0.0243 0.6537 1.0000
7.500 0.4219 0.09419 0.08306 -0.0233 0.6433 1.0000
7.750 0.4521 0.09757 0.08645 -0.0248 0.6337 1.0000
8.000 0.4465 0.09841 0.08729 -0.0230 0.6222 1.0000
8.250 0.4853 0.10303 0.09192 -0.0254 0.6148 1.0000
8.500 0.4733 0.10300 0.09189 -0.0230 0.6019 1.0000
8.750 0.4928 0.10637 0.09529 -0.0238 0.5951 1.0000
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Polar data table (+)
Polar graphs
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