EPPLER 378 AIRFOIL (e378-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: EPPLER 378 AIRFOIL (e378-il) Reynolds number: 100,000 Max Cl/Cd: 65.11 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e378-il-100000-n5.txt Download as CSV file: xf-e378-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2747 0.11517 0.11081 -0.0034 1.0000 0.0204
-8.000 -0.2660 0.11321 0.10892 -0.0052 1.0000 0.0204
-7.750 -0.2577 0.11134 0.10714 -0.0070 1.0000 0.0205
-7.500 -0.2447 0.10911 0.10500 -0.0100 0.9578 0.0205
-7.250 -0.2266 0.10197 0.09785 -0.0110 0.9220 0.0209
-7.000 -0.2086 0.09733 0.09309 -0.0129 0.8714 0.0214
-6.750 -0.1968 0.09445 0.09012 -0.0141 0.8399 0.0219
-6.500 -0.1859 0.09207 0.08761 -0.0149 0.8100 0.0223
-6.250 -0.1732 0.08961 0.08508 -0.0165 0.7952 0.0229
-6.000 -0.1590 0.08713 0.08255 -0.0187 0.7843 0.0235
-5.750 -0.1451 0.08483 0.08013 -0.0201 0.7648 0.0242
-5.500 -0.1284 0.08232 0.07757 -0.0227 0.7509 0.0251
-5.250 -0.1083 0.07996 0.07520 -0.0262 0.7391 0.0269
-5.000 -0.0733 0.07968 0.07488 -0.0351 0.7281 0.0285
-4.750 -0.0394 0.07873 0.07382 -0.0428 0.7173 0.0288
-4.500 -0.0340 0.07285 0.06795 -0.0402 0.7102 0.0294
-4.250 -0.0197 0.06912 0.06419 -0.0404 0.7036 0.0304
-4.000 0.0007 0.06640 0.06137 -0.0423 0.6952 0.0315
-3.750 0.0246 0.06378 0.05865 -0.0450 0.6870 0.0332
-3.500 0.0518 0.06125 0.05601 -0.0485 0.6782 0.0353
-3.250 0.0872 0.05911 0.05370 -0.0539 0.6700 0.0382
-3.000 0.1415 0.05816 0.05256 -0.0637 0.6614 0.0395
-2.750 0.1814 0.05595 0.05015 -0.0692 0.6544 0.0397
-2.500 0.2014 0.05156 0.04579 -0.0703 0.6473 0.0404
-2.250 0.2218 0.04822 0.04240 -0.0710 0.6412 0.0415
-2.000 0.2526 0.04563 0.03974 -0.0737 0.6339 0.0426
-1.750 0.2857 0.04328 0.03725 -0.0767 0.6279 0.0445
-1.500 0.3437 0.04258 0.03621 -0.0841 0.6210 0.0521
-1.250 0.3814 0.04016 0.03360 -0.0873 0.6150 0.0523
-1.000 0.4024 0.03576 0.02914 -0.0877 0.6100 0.0363
-0.750 0.4409 0.03326 0.02646 -0.0907 0.6036 0.0339
-0.500 0.4795 0.03089 0.02381 -0.0934 0.5986 0.0334
-0.250 0.5207 0.02863 0.02124 -0.0962 0.5927 0.0385
0.000 0.5610 0.02578 0.01798 -0.0984 0.5874 0.0398
0.250 0.5878 0.02516 0.01721 -0.0986 0.5823 0.0457
0.500 0.6253 0.02273 0.01432 -0.1001 0.5765 0.0504
0.750 0.6595 0.02049 0.01149 -0.1010 0.5717 0.0538
1.000 0.6884 0.01992 0.01065 -0.1010 0.5665 0.0631
1.250 0.7177 0.01925 0.00976 -0.1011 0.5606 0.0711
1.500 0.7457 0.01885 0.00911 -0.1008 0.5559 0.0834
1.750 0.7735 0.01862 0.00872 -0.1007 0.5504 0.0963
2.000 0.8019 0.01850 0.00847 -0.1007 0.5448 0.1094
2.250 0.8313 0.01833 0.00805 -0.1006 0.5405 0.1200
2.500 0.8594 0.01836 0.00807 -0.1007 0.5344 0.1332
2.750 0.8872 0.01830 0.00798 -0.1005 0.5292 0.1425
3.000 0.9144 0.01830 0.00791 -0.1002 0.5245 0.1535
3.250 0.9413 0.01841 0.00806 -0.1000 0.5186 0.1700
3.500 0.9679 0.01848 0.00809 -0.0997 0.5138 0.1854
3.750 0.9944 0.01862 0.00828 -0.0994 0.5085 0.2036
4.000 1.0209 0.01878 0.00854 -0.0991 0.5028 0.2247
4.250 1.0472 0.01891 0.00867 -0.0988 0.4983 0.2488
4.500 1.0735 0.01912 0.00901 -0.0986 0.4921 0.2782
4.750 1.0996 0.01926 0.00926 -0.0983 0.4866 0.3192
5.000 1.1300 0.01874 0.00947 -0.0990 0.4811 1.0000
5.250 1.1559 0.01907 0.00987 -0.0986 0.4742 1.0000
5.500 1.1817 0.01929 0.01001 -0.0981 0.4690 1.0000
5.750 1.2071 0.01963 0.01049 -0.0978 0.4608 1.0000
6.000 1.2327 0.01983 0.01065 -0.0972 0.4547 1.0000
6.250 1.2577 0.02016 0.01122 -0.0968 0.4458 1.0000
6.500 1.2829 0.02040 0.01151 -0.0962 0.4382 1.0000
6.750 1.3077 0.02064 0.01186 -0.0957 0.4290 1.0000
7.000 1.3322 0.02092 0.01229 -0.0952 0.4190 1.0000
7.250 1.3567 0.02114 0.01262 -0.0946 0.4088 1.0000
7.500 1.3809 0.02136 0.01300 -0.0939 0.3978 1.0000
7.750 1.4046 0.02162 0.01341 -0.0933 0.3848 1.0000
8.000 1.4279 0.02193 0.01389 -0.0926 0.3700 1.0000
8.250 1.4506 0.02231 0.01446 -0.0920 0.3528 1.0000
8.500 1.4726 0.02273 0.01503 -0.0912 0.3329 1.0000
8.750 1.4934 0.02327 0.01567 -0.0904 0.3088 1.0000
9.000 1.5124 0.02400 0.01651 -0.0895 0.2783 1.0000
9.250 1.5287 0.02507 0.01751 -0.0884 0.2431 1.0000
9.500 1.5413 0.02654 0.01888 -0.0872 0.2072 1.0000
9.750 1.5508 0.02832 0.02055 -0.0859 0.1761 1.0000
10.000 1.5575 0.03027 0.02245 -0.0844 0.1507 1.0000
10.250 1.5624 0.03225 0.02446 -0.0828 0.1303 1.0000
10.500 1.5624 0.03449 0.02670 -0.0810 0.1140 1.0000
10.750 1.5570 0.03691 0.02916 -0.0790 0.1020 1.0000
11.000 1.5510 0.03973 0.03205 -0.0778 0.0917 1.0000
11.250 1.5440 0.04299 0.03536 -0.0771 0.0837 1.0000
11.500 1.5377 0.04642 0.03886 -0.0768 0.0757 1.0000
11.750 1.5317 0.05003 0.04264 -0.0768 0.0683 1.0000
12.000 1.5238 0.05400 0.04666 -0.0770 0.0628 1.0000
12.250 1.5183 0.05778 0.05057 -0.0771 0.0566 1.0000
12.500 1.5100 0.06201 0.05488 -0.0776 0.0520 1.0000
12.750 1.5030 0.06611 0.05908 -0.0778 0.0477 1.0000
13.000 1.4964 0.07028 0.06341 -0.0783 0.0440 1.0000
13.250 1.4871 0.07487 0.06807 -0.0790 0.0410 1.0000
13.500 1.4797 0.07926 0.07257 -0.0795 0.0377 1.0000
13.750 1.4736 0.08371 0.07719 -0.0804 0.0340 1.0000
14.000 1.4650 0.08870 0.08227 -0.0817 0.0314 1.0000
14.250 1.4570 0.09353 0.08715 -0.0826 0.0292 1.0000
14.500 1.4526 0.09804 0.09190 -0.0836 0.0265 1.0000
14.750 1.4455 0.10324 0.09725 -0.0853 0.0241 1.0000
15.000 1.4364 0.10895 0.10305 -0.0876 0.0222 1.0000
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Polar data table (+)
Polar graphs
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