EPPLER 378 AIRFOIL (e378-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: EPPLER 378 AIRFOIL (e378-il) Reynolds number: 200,000 Max Cl/Cd: 90.72 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e378-il-200000-n5.txt Download as CSV file: xf-e378-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2535 0.10500 0.10148 -0.0042 0.8125 0.0122
-7.750 -0.2461 0.10275 0.09906 -0.0044 0.7802 0.0125
-7.500 -0.2384 0.10056 0.09672 -0.0047 0.7550 0.0127
-7.250 -0.2280 0.09808 0.09430 -0.0064 0.7441 0.0130
-7.000 -0.2179 0.09578 0.09204 -0.0078 0.7262 0.0133
-6.500 -0.1957 0.09152 0.08761 -0.0112 0.7028 0.0137
-6.250 -0.1809 0.08936 0.08540 -0.0140 0.6962 0.0138
-6.000 -0.1652 0.08713 0.08306 -0.0169 0.6868 0.0139
-5.750 -0.1480 0.08477 0.08066 -0.0198 0.6782 0.0139
-5.500 -0.1296 0.08242 0.07821 -0.0230 0.6672 0.0140
-5.250 -0.1080 0.07985 0.07560 -0.0270 0.6596 0.0140
-5.000 -0.0853 0.07725 0.07294 -0.0310 0.6513 0.0141
-4.750 -0.0612 0.07446 0.07011 -0.0350 0.6439 0.0141
-4.500 -0.0368 0.07158 0.06718 -0.0386 0.6372 0.0141
-4.250 -0.0231 0.06713 0.06274 -0.0390 0.6313 0.0144
-4.000 -0.0031 0.06407 0.05962 -0.0409 0.6249 0.0147
-3.750 0.0202 0.06123 0.05674 -0.0435 0.6182 0.0152
-3.500 0.0470 0.05855 0.05398 -0.0469 0.6122 0.0159
-3.250 0.0766 0.05582 0.05118 -0.0507 0.6055 0.0168
-3.000 0.1235 0.05378 0.04900 -0.0583 0.5994 0.0202
-2.750 0.1654 0.05063 0.04574 -0.0648 0.5936 0.0208
-2.500 0.1843 0.04731 0.04240 -0.0653 0.5879 0.0215
-2.250 0.2143 0.04480 0.03978 -0.0681 0.5827 0.0224
-2.000 0.2487 0.04233 0.03723 -0.0715 0.5765 0.0234
-1.750 0.2855 0.03982 0.03459 -0.0753 0.5713 0.0238
-1.500 0.3263 0.03674 0.03132 -0.0796 0.5664 0.0181
-1.250 0.3662 0.03388 0.02831 -0.0834 0.5609 0.0162
-1.000 0.4087 0.03083 0.02503 -0.0873 0.5561 0.0153
-0.750 0.4461 0.02849 0.02252 -0.0899 0.5512 0.0160
-0.500 0.4864 0.02588 0.01967 -0.0927 0.5462 0.0198
-0.250 0.5297 0.02190 0.01526 -0.0957 0.5421 0.0205
0.000 0.5651 0.01936 0.01238 -0.0972 0.5374 0.0228
0.250 0.6016 0.01552 0.00776 -0.0987 0.5314 0.0293
0.500 0.6290 0.01521 0.00733 -0.0984 0.5268 0.0348
0.750 0.6571 0.01440 0.00622 -0.0981 0.5216 0.0392
1.000 0.6841 0.01398 0.00574 -0.0976 0.5165 0.0441
1.250 0.7106 0.01379 0.00538 -0.0970 0.5122 0.0523
1.500 0.7375 0.01371 0.00530 -0.0966 0.5074 0.0639
1.750 0.7641 0.01366 0.00522 -0.0962 0.5026 0.0741
2.000 0.7903 0.01371 0.00523 -0.0957 0.4984 0.0857
2.250 0.8168 0.01367 0.00515 -0.0952 0.4938 0.0944
2.500 0.8434 0.01365 0.00513 -0.0948 0.4891 0.1016
2.750 0.8697 0.01369 0.00514 -0.0943 0.4848 0.1110
3.000 0.8966 0.01371 0.00514 -0.0939 0.4803 0.1207
3.250 0.9233 0.01376 0.00520 -0.0936 0.4754 0.1306
3.500 0.9497 0.01384 0.00527 -0.0932 0.4710 0.1415
3.750 0.9768 0.01392 0.00535 -0.0930 0.4665 0.1562
4.000 1.0043 0.01398 0.00547 -0.0929 0.4613 0.1724
4.250 1.0315 0.01407 0.00555 -0.0927 0.4566 0.1891
4.500 1.0588 0.01417 0.00570 -0.0926 0.4514 0.2091
4.750 1.0860 0.01427 0.00585 -0.0924 0.4454 0.2311
5.000 1.1127 0.01440 0.00600 -0.0922 0.4398 0.2585
5.250 1.1397 0.01451 0.00628 -0.0920 0.4325 0.2940
5.500 1.1663 0.01460 0.00657 -0.0918 0.4262 0.4187
6.000 1.2342 0.01386 0.00631 -0.0952 0.4104 1.0000
6.250 1.2600 0.01406 0.00660 -0.0948 0.4014 1.0000
6.500 1.2858 0.01427 0.00687 -0.0945 0.3922 1.0000
6.750 1.3113 0.01450 0.00713 -0.0941 0.3824 1.0000
7.000 1.3365 0.01475 0.00741 -0.0937 0.3710 1.0000
7.250 1.3617 0.01501 0.00775 -0.0933 0.3582 1.0000
7.500 1.3865 0.01532 0.00816 -0.0929 0.3441 1.0000
7.750 1.4109 0.01567 0.00856 -0.0925 0.3272 1.0000
8.000 1.4347 0.01610 0.00901 -0.0920 0.3046 1.0000
8.250 1.4573 0.01667 0.00955 -0.0915 0.2768 1.0000
8.500 1.4785 0.01746 0.01025 -0.0910 0.2428 1.0000
8.750 1.4977 0.01852 0.01120 -0.0903 0.2060 1.0000
9.000 1.5160 0.01966 0.01225 -0.0896 0.1747 1.0000
9.250 1.5335 0.02085 0.01338 -0.0888 0.1482 1.0000
9.500 1.5492 0.02218 0.01463 -0.0879 0.1222 1.0000
10.000 1.5762 0.02502 0.01736 -0.0857 0.0802 1.0000
10.250 1.5876 0.02646 0.01882 -0.0844 0.0663 1.0000
10.500 1.5974 0.02793 0.02034 -0.0829 0.0564 1.0000
10.750 1.6031 0.02957 0.02211 -0.0812 0.0488 1.0000
11.000 1.6037 0.03133 0.02394 -0.0790 0.0425 1.0000
11.250 1.6018 0.03355 0.02627 -0.0775 0.0377 1.0000
11.500 1.6001 0.03610 0.02889 -0.0767 0.0322 1.0000
11.750 1.5975 0.03891 0.03180 -0.0760 0.0276 1.0000
12.000 1.5951 0.04184 0.03479 -0.0756 0.0230 1.0000
12.250 1.5911 0.04521 0.03824 -0.0755 0.0196 1.0000
12.500 1.5881 0.04851 0.04166 -0.0756 0.0165 1.0000
12.750 1.5816 0.05235 0.04559 -0.0757 0.0147 1.0000
13.000 1.5757 0.05625 0.04962 -0.0761 0.0129 1.0000
13.250 1.5706 0.06005 0.05352 -0.0764 0.0104 1.0000
13.500 1.5607 0.06461 0.05817 -0.0771 0.0092 1.0000
13.750 1.5528 0.06904 0.06275 -0.0778 0.0083 1.0000
14.000 1.5458 0.07335 0.06722 -0.0786 0.0069 1.0000
14.250 1.5374 0.07815 0.07217 -0.0797 0.0063 1.0000
14.500 1.5273 0.08335 0.07750 -0.0812 0.0059 1.0000
14.750 1.5148 0.08917 0.08347 -0.0829 0.0055 1.0000
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Polar data table (+)
Polar graphs
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