EPPLER 379 AIRFOIL (e379-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 379 AIRFOIL (e379-il) Reynolds number: 500,000 Max Cl/Cd: 118.57 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e379-il-500000-n5.txt Download as CSV file: xf-e379-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 379 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3200 0.11769 0.11514 0.0057 0.8086 0.0023
-9.000 -0.3121 0.11532 0.11263 0.0050 0.7779 0.0023
-8.750 -0.3038 0.11289 0.11011 0.0039 0.7531 0.0023
-8.500 -0.2953 0.11042 0.10757 0.0029 0.7326 0.0023
-8.250 -0.2868 0.10799 0.10507 0.0019 0.7141 0.0023
-8.000 -0.2784 0.10568 0.10270 0.0009 0.6983 0.0023
-7.750 -0.2706 0.10334 0.10031 0.0000 0.6843 0.0023
-7.500 -0.2612 0.10102 0.09795 -0.0012 0.6717 0.0023
-7.250 -0.2493 0.09846 0.09535 -0.0032 0.6604 0.0023
-7.000 -0.2362 0.09585 0.09270 -0.0052 0.6502 0.0023
-6.750 -0.2222 0.09324 0.09004 -0.0074 0.6395 0.0023
-6.500 -0.2070 0.09058 0.08735 -0.0098 0.6304 0.0023
-6.250 -0.1907 0.08787 0.08461 -0.0124 0.6218 0.0023
-6.000 -0.1734 0.08518 0.08187 -0.0150 0.6143 0.0023
-5.750 -0.1547 0.08241 0.07907 -0.0179 0.6062 0.0023
-5.500 -0.1352 0.07970 0.07631 -0.0208 0.5992 0.0023
-5.250 -0.1140 0.07687 0.07342 -0.0239 0.5925 0.0023
-5.000 -0.0918 0.07407 0.07057 -0.0271 0.5861 0.0023
-4.750 -0.0683 0.07127 0.06773 -0.0304 0.5799 0.0023
-4.500 -0.0436 0.06847 0.06486 -0.0337 0.5741 0.0024
-4.250 -0.0175 0.06563 0.06198 -0.0372 0.5683 0.0024
-4.000 0.0097 0.06285 0.05915 -0.0407 0.5629 0.0024
-3.750 0.0384 0.06005 0.05629 -0.0442 0.5578 0.0024
-3.500 0.0681 0.05728 0.05347 -0.0478 0.5523 0.0024
-3.250 0.0955 0.05316 0.04930 -0.0512 0.5476 0.0025
-3.000 0.1204 0.04967 0.04577 -0.0539 0.5430 0.0027
-2.750 0.1495 0.04707 0.04311 -0.0569 0.5381 0.0031
-2.250 0.2143 0.04237 0.03826 -0.0633 0.5286 0.0043
-2.000 0.2500 0.04042 0.03622 -0.0662 0.5238 0.0065
-1.750 0.2892 0.03891 0.03459 -0.0692 0.5197 0.0069
-1.500 0.3289 0.03762 0.03320 -0.0721 0.5150 0.0072
-1.250 0.3622 0.03552 0.03097 -0.0743 0.5104 0.0072
-0.750 0.4281 0.03160 0.02684 -0.0779 0.5023 0.0072
-0.500 0.4607 0.02975 0.02489 -0.0794 0.4979 0.0072
-0.250 0.4930 0.02801 0.02302 -0.0807 0.4937 0.0073
1.000 0.6502 0.02000 0.01441 -0.0846 0.4733 0.0073
1.250 0.6802 0.01802 0.01220 -0.0852 0.4693 0.0066
1.750 0.7410 0.01548 0.00932 -0.0854 0.4615 0.0056
2.000 0.7713 0.01423 0.00788 -0.0851 0.4573 0.0053
2.250 0.8012 0.01288 0.00627 -0.0847 0.4535 0.0050
2.500 0.8306 0.01133 0.00440 -0.0842 0.4499 0.0048
2.750 0.8583 0.01026 0.00303 -0.0837 0.4456 0.0049
3.000 0.8850 0.00976 0.00239 -0.0833 0.4413 0.0054
3.250 0.9118 0.00973 0.00234 -0.0831 0.4371 0.0066
3.750 0.9656 0.00979 0.00240 -0.0828 0.4273 0.0216
4.000 0.9924 0.00981 0.00240 -0.0827 0.4223 0.0212
4.250 1.0192 0.00984 0.00242 -0.0825 0.4158 0.0209
4.500 1.0459 0.00991 0.00246 -0.0823 0.4092 0.0208
4.750 1.0727 0.00998 0.00253 -0.0822 0.4020 0.0210
5.000 1.0993 0.01009 0.00262 -0.0821 0.3954 0.0220
5.250 1.1258 0.01013 0.00285 -0.0819 0.3879 0.0936
5.500 1.1501 0.00970 0.00315 -0.0816 0.3807 0.7060
6.000 1.2037 0.01199 0.00449 -0.0840 0.1518 1.0000
6.250 1.2251 0.01323 0.00531 -0.0837 0.0829 1.0000
6.500 1.2444 0.01489 0.00653 -0.0833 0.0015 1.0000
6.750 1.2692 0.01525 0.00690 -0.0830 0.0013 1.0000
7.000 1.2936 0.01567 0.00738 -0.0826 0.0012 1.0000
7.250 1.3176 0.01612 0.00809 -0.0822 0.0014 1.0000
7.500 1.3410 0.01670 0.00880 -0.0817 0.0014 1.0000
7.750 1.3637 0.01739 0.00967 -0.0811 0.0014 1.0000
8.000 1.3851 0.01825 0.01073 -0.0804 0.0014 1.0000
8.250 1.4048 0.01934 0.01202 -0.0795 0.0014 1.0000
8.500 1.4218 0.02073 0.01361 -0.0784 0.0014 1.0000
8.750 1.4356 0.02237 0.01544 -0.0770 0.0015 1.0000
9.000 1.4459 0.02423 0.01748 -0.0754 0.0015 1.0000
9.250 1.4519 0.02629 0.01972 -0.0733 0.0015 1.0000
9.500 1.4542 0.02843 0.02202 -0.0709 0.0016 1.0000
9.750 1.4496 0.03065 0.02437 -0.0679 0.0016 1.0000
10.000 1.4452 0.03332 0.02719 -0.0658 0.0017 1.0000
10.250 1.4412 0.03648 0.03051 -0.0638 0.0017 1.0000
12.250 1.4611 0.06003 0.05561 -0.0562 0.0035 1.0000
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Polar data table (+)
Polar graphs
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