EPPLER 378 AIRFOIL (e378-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 378 AIRFOIL (e378-il) Reynolds number: 500,000 Max Cl/Cd: 124.67 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e378-il-500000-n5.txt Download as CSV file: xf-e378-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 378 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.2403 0.10017 0.09690 -0.0066 0.6541 0.0056
-7.250 -0.2320 0.09776 0.09449 -0.0075 0.6466 0.0056
-7.000 -0.2226 0.09542 0.09212 -0.0087 0.6381 0.0056
-6.750 -0.2105 0.09281 0.08947 -0.0106 0.6286 0.0056
-6.500 -0.1968 0.09013 0.08678 -0.0130 0.6223 0.0056
-6.250 -0.1830 0.08745 0.08407 -0.0149 0.6138 0.0056
-6.000 -0.1703 0.08390 0.08050 -0.0167 0.6073 0.0057
-5.750 -0.1547 0.08106 0.07764 -0.0190 0.6007 0.0058
-5.500 -0.1388 0.07835 0.07491 -0.0211 0.5942 0.0059
-5.250 -0.1204 0.07571 0.07223 -0.0239 0.5876 0.0060
-5.000 -0.1009 0.07305 0.06952 -0.0267 0.5820 0.0062
-4.750 -0.0791 0.07031 0.06675 -0.0300 0.5760 0.0063
-4.500 -0.0570 0.06760 0.06401 -0.0330 0.5702 0.0066
-4.250 -0.0322 0.06482 0.06119 -0.0367 0.5649 0.0068
-4.000 -0.0064 0.06199 0.05832 -0.0404 0.5596 0.0072
-3.750 0.0215 0.05912 0.05539 -0.0442 0.5545 0.0079
-3.500 0.0557 0.05617 0.05239 -0.0493 0.5492 0.0087
-3.250 0.0907 0.05317 0.04931 -0.0544 0.5442 0.0088
-3.000 0.1242 0.05014 0.04619 -0.0587 0.5397 0.0089
-2.750 0.1586 0.04695 0.04294 -0.0630 0.5349 0.0089
-2.500 0.1877 0.04392 0.03985 -0.0660 0.5301 0.0083
-2.250 0.2204 0.04171 0.03756 -0.0694 0.5256 0.0106
-2.000 0.2673 0.03953 0.03526 -0.0748 0.5210 0.0138
-1.250 0.3790 0.02987 0.02522 -0.0855 0.5082 0.0086
-1.000 0.4183 0.02698 0.02218 -0.0887 0.5039 0.0084
-0.750 0.4620 0.02319 0.01814 -0.0924 0.5002 0.0085
-0.500 0.5210 0.01221 0.00593 -0.0989 0.4972 0.0089
-0.250 0.5463 0.01119 0.00461 -0.0980 0.4925 0.0103
0.000 0.5737 0.01095 0.00428 -0.0978 0.4878 0.0121
0.250 0.6010 0.01056 0.00373 -0.0973 0.4836 0.0130
0.500 0.6281 0.01023 0.00331 -0.0968 0.4795 0.0146
0.750 0.6549 0.00999 0.00302 -0.0962 0.4750 0.0208
1.000 0.6816 0.00989 0.00289 -0.0957 0.4707 0.0310
1.250 0.7085 0.00985 0.00287 -0.0954 0.4667 0.0431
1.500 0.7357 0.00985 0.00285 -0.0951 0.4624 0.0516
1.750 0.7626 0.00982 0.00279 -0.0947 0.4580 0.0581
2.000 0.7895 0.00985 0.00277 -0.0943 0.4539 0.0648
2.250 0.8166 0.00982 0.00276 -0.0940 0.4497 0.0717
2.500 0.8436 0.00985 0.00275 -0.0937 0.4451 0.0783
2.750 0.8775 0.00957 0.00218 -0.0951 0.4417 0.0876
3.000 0.9047 0.00959 0.00221 -0.0949 0.4374 0.0947
3.250 0.9319 0.00963 0.00227 -0.0947 0.4325 0.1035
3.500 0.9589 0.00970 0.00235 -0.0944 0.4277 0.1140
3.750 0.9860 0.00975 0.00243 -0.0942 0.4226 0.1238
4.000 1.0130 0.00983 0.00253 -0.0940 0.4165 0.1339
4.250 1.0398 0.00992 0.00264 -0.0937 0.4103 0.1458
4.500 1.0667 0.01000 0.00275 -0.0935 0.4035 0.1602
4.750 1.0935 0.01010 0.00289 -0.0933 0.3972 0.1745
5.000 1.1203 0.01019 0.00303 -0.0931 0.3898 0.1919
5.250 1.1469 0.01032 0.00322 -0.0929 0.3821 0.2117
5.500 1.1734 0.01044 0.00339 -0.0927 0.3735 0.2325
5.750 1.1999 0.01057 0.00358 -0.0925 0.3650 0.2612
6.000 1.2261 0.01073 0.00379 -0.0922 0.3551 0.2968
6.250 1.2510 0.01055 0.00408 -0.0919 0.3441 0.6991
6.500 1.2866 0.01032 0.00432 -0.0938 0.3299 1.0000
6.750 1.3122 0.01061 0.00457 -0.0935 0.3149 1.0000
7.000 1.3374 0.01093 0.00487 -0.0931 0.2971 1.0000
7.250 1.3537 0.01161 0.00521 -0.0910 0.2803 0.7851
7.500 1.3879 0.01190 0.00571 -0.0930 0.2470 1.0000
7.750 1.4112 0.01258 0.00625 -0.0926 0.2150 1.0000
8.000 1.4331 0.01348 0.00695 -0.0922 0.1776 1.0000
8.250 1.4552 0.01430 0.00764 -0.0917 0.1477 1.0000
8.500 1.4774 0.01504 0.00829 -0.0913 0.1262 1.0000
8.750 1.4991 0.01582 0.00902 -0.0908 0.1051 1.0000
9.000 1.5193 0.01677 0.00985 -0.0902 0.0815 1.0000
9.250 1.5389 0.01773 0.01071 -0.0895 0.0628 1.0000
9.500 1.5588 0.01858 0.01153 -0.0888 0.0502 1.0000
9.750 1.5777 0.01949 0.01242 -0.0881 0.0387 1.0000
10.000 1.5956 0.02045 0.01336 -0.0872 0.0292 1.0000
10.250 1.6127 0.02143 0.01434 -0.0863 0.0222 1.0000
10.500 1.6288 0.02241 0.01540 -0.0852 0.0169 1.0000
10.750 1.6419 0.02361 0.01662 -0.0839 0.0110 1.0000
11.000 1.6495 0.02518 0.01819 -0.0822 0.0055 1.0000
11.250 1.6556 0.02659 0.01968 -0.0802 0.0039 1.0000
11.500 1.6551 0.02823 0.02142 -0.0778 0.0033 1.0000
11.750 1.6551 0.03024 0.02356 -0.0763 0.0028 1.0000
12.000 1.6560 0.03252 0.02598 -0.0755 0.0026 1.0000
12.250 1.6558 0.03503 0.02862 -0.0747 0.0023 1.0000
12.500 1.6565 0.03755 0.03126 -0.0741 0.0023 1.0000
12.750 1.6535 0.04079 0.03464 -0.0741 0.0021 1.0000
13.000 1.6504 0.04413 0.03811 -0.0742 0.0020 1.0000
13.250 1.6442 0.04793 0.04205 -0.0744 0.0018 1.0000
13.500 1.6373 0.05190 0.04618 -0.0746 0.0017 1.0000
13.750 1.6271 0.05641 0.05084 -0.0752 0.0016 1.0000
14.000 1.6186 0.06078 0.05536 -0.0759 0.0016 1.0000
14.250 1.6126 0.06479 0.05949 -0.0763 0.0015 1.0000
14.500 1.6070 0.06891 0.06375 -0.0771 0.0014 1.0000
14.750 1.6008 0.07328 0.06825 -0.0781 0.0014 1.0000
15.000 1.5930 0.07803 0.07313 -0.0792 0.0013 1.0000
15.250 1.5852 0.08294 0.07816 -0.0805 0.0013 1.0000
15.500 1.5789 0.08771 0.08306 -0.0820 0.0012 1.0000
15.750 1.5696 0.09317 0.08866 -0.0838 0.0012 1.0000
16.000 1.5632 0.09821 0.09382 -0.0854 0.0011 1.0000
16.250 1.5525 0.10416 0.09991 -0.0876 0.0011 1.0000
16.500 1.5437 0.10991 0.10579 -0.0898 0.0010 1.0000
16.750 1.5348 0.11581 0.11182 -0.0922 0.0010 1.0000
17.000 1.5253 0.12193 0.11807 -0.0949 0.0010 1.0000
17.250 1.5151 0.12832 0.12460 -0.0978 0.0009 1.0000
17.500 1.5054 0.13477 0.13117 -0.1008 0.0009 1.0000
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Polar data table (+)
Polar graphs
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