EPPLER 379 AIRFOIL (e379-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 379 AIRFOIL (e379-il) Reynolds number: 100,000 Max Cl/Cd: 66.77 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e379-il-100000-n5.txt Download as CSV file: xf-e379-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3733 0.13875 0.13416 0.0118 1.0000 0.0075
-10.250 -0.3630 0.13326 0.12868 0.0110 1.0000 0.0076
-10.000 -0.3537 0.12905 0.12450 0.0100 1.0000 0.0077
-9.750 -0.3445 0.12555 0.12103 0.0088 1.0000 0.0078
-9.500 -0.3355 0.12229 0.11781 0.0076 1.0000 0.0079
-9.250 -0.3265 0.11917 0.11466 0.0063 1.0000 0.0081
-9.000 -0.3173 0.11633 0.11186 0.0049 1.0000 0.0082
-8.750 -0.3081 0.11350 0.10908 0.0036 1.0000 0.0083
-8.500 -0.2989 0.11074 0.10637 0.0022 1.0000 0.0084
-8.250 -0.2897 0.10812 0.10381 0.0009 1.0000 0.0086
-8.000 -0.2802 0.10558 0.10132 -0.0005 1.0000 0.0087
-7.750 -0.2711 0.10303 0.09884 -0.0019 1.0000 0.0089
-7.500 -0.2615 0.10062 0.09650 -0.0034 1.0000 0.0090
-7.250 -0.2505 0.09808 0.09403 -0.0052 1.0000 0.0092
-7.000 -0.2379 0.09548 0.09150 -0.0075 1.0000 0.0094
-6.750 -0.2149 0.09224 0.08826 -0.0124 0.9357 0.0096
-6.500 -0.1916 0.08906 0.08500 -0.0169 0.8913 0.0099
-6.250 -0.1750 0.08647 0.08232 -0.0193 0.8570 0.0102
-6.000 -0.1597 0.08408 0.07983 -0.0212 0.8303 0.0104
-5.750 -0.1438 0.08164 0.07731 -0.0232 0.8076 0.0107
-5.500 -0.1267 0.07925 0.07475 -0.0254 0.7884 0.0110
-5.250 -0.1079 0.07671 0.07213 -0.0279 0.7720 0.0114
-5.000 -0.0876 0.07418 0.06953 -0.0306 0.7568 0.0118
-4.750 -0.0658 0.07166 0.06693 -0.0335 0.7435 0.0123
-4.500 -0.0420 0.06918 0.06436 -0.0367 0.7311 0.0133
-4.250 -0.0140 0.06699 0.06208 -0.0405 0.7196 0.0141
-4.000 0.0177 0.06516 0.06012 -0.0449 0.7091 0.0145
-3.750 0.0538 0.06358 0.05840 -0.0501 0.6987 0.0146
-3.500 0.0875 0.06155 0.05625 -0.0545 0.6890 0.0147
-3.250 0.1062 0.05755 0.05223 -0.0556 0.6809 0.0149
-3.000 0.1274 0.05404 0.04866 -0.0572 0.6725 0.0155
-2.750 0.1570 0.05140 0.04592 -0.0603 0.6644 0.0163
-2.500 0.1887 0.04903 0.04343 -0.0634 0.6570 0.0172
-2.250 0.2227 0.04682 0.04111 -0.0667 0.6490 0.0183
-2.000 0.2600 0.04513 0.03923 -0.0701 0.6424 0.0194
-1.750 0.3055 0.04455 0.03844 -0.0743 0.6344 0.0201
-1.500 0.3299 0.04120 0.03500 -0.0758 0.6286 0.0207
-1.250 0.3577 0.03865 0.03231 -0.0776 0.6213 0.0221
-1.000 0.3900 0.03685 0.03034 -0.0795 0.6156 0.0239
-0.750 0.4248 0.03536 0.02871 -0.0816 0.6087 0.0261
-0.500 0.4672 0.03528 0.02830 -0.0835 0.6028 0.0279
-0.250 0.4932 0.03243 0.02541 -0.0849 0.5968 0.0291
0.000 0.5224 0.03072 0.02357 -0.0859 0.5910 0.0322
0.250 0.5615 0.03071 0.02322 -0.0869 0.5855 0.0374
0.500 0.5871 0.02826 0.02074 -0.0879 0.5795 0.0404
0.750 0.6218 0.02780 0.01997 -0.0883 0.5747 0.0478
1.000 0.6525 0.02646 0.01840 -0.0889 0.5687 0.0480
1.250 0.6826 0.02459 0.01629 -0.0891 0.5637 0.0227
1.500 0.7154 0.02401 0.01539 -0.0889 0.5589 0.0279
1.750 0.7439 0.02343 0.01467 -0.0892 0.5530 0.0469
2.000 0.7733 0.02197 0.01296 -0.0891 0.5485 0.0357
2.250 0.8030 0.02097 0.01175 -0.0890 0.5433 0.0327
2.500 0.8330 0.02007 0.01057 -0.0888 0.5381 0.0322
2.750 0.8618 0.01926 0.00942 -0.0883 0.5340 0.0348
3.000 0.8928 0.01882 0.00871 -0.0887 0.5281 0.0471
3.250 0.9212 0.01832 0.00799 -0.0885 0.5231 0.0482
3.500 0.9476 0.01814 0.00763 -0.0881 0.5187 0.0503
3.750 0.9741 0.01819 0.00766 -0.0879 0.5126 0.0546
4.000 1.0007 0.01824 0.00764 -0.0876 0.5079 0.0740
4.500 1.0590 0.01776 0.00817 -0.0887 0.4966 1.0000
4.750 1.0848 0.01802 0.00831 -0.0883 0.4922 1.0000
5.000 1.1105 0.01837 0.00872 -0.0881 0.4854 1.0000
5.250 1.1361 0.01862 0.00905 -0.0877 0.4803 1.0000
5.500 1.1615 0.01896 0.00947 -0.0875 0.4734 1.0000
5.750 1.1869 0.01920 0.00971 -0.0871 0.4671 1.0000
6.000 1.2120 0.01951 0.01013 -0.0868 0.4593 1.0000
6.250 1.2372 0.01970 0.01034 -0.0863 0.4525 1.0000
6.500 1.2620 0.02002 0.01084 -0.0859 0.4436 1.0000
6.750 1.2870 0.02024 0.01116 -0.0855 0.4358 1.0000
7.000 1.3117 0.02046 0.01152 -0.0850 0.4268 1.0000
7.250 1.3360 0.02074 0.01242 -0.0845 0.4163 1.0000
7.500 1.3596 0.02064 0.01242 -0.0836 0.3968 1.0000
7.750 1.3782 0.02064 0.01213 -0.0824 0.3173 1.0000
8.000 1.3899 0.02249 0.01325 -0.0813 0.2050 1.0000
8.250 1.3952 0.02553 0.01559 -0.0802 0.1067 1.0000
8.500 1.3875 0.02988 0.01898 -0.0784 0.0088 1.0000
8.750 1.3981 0.03163 0.02090 -0.0769 0.0060 1.0000
9.000 1.4081 0.03331 0.02286 -0.0755 0.0056 1.0000
9.250 1.4147 0.03519 0.02503 -0.0738 0.0053 1.0000
9.500 1.4164 0.03724 0.02735 -0.0720 0.0051 1.0000
9.750 1.4145 0.03966 0.03002 -0.0704 0.0050 1.0000
10.000 1.4116 0.04250 0.03311 -0.0694 0.0050 1.0000
10.250 1.4078 0.04571 0.03656 -0.0689 0.0049 1.0000
10.500 1.4041 0.04908 0.04016 -0.0688 0.0049 1.0000
10.750 1.3986 0.05283 0.04414 -0.0688 0.0048 1.0000
11.000 1.3934 0.05664 0.04816 -0.0689 0.0048 1.0000
11.250 1.3875 0.06064 0.05238 -0.0691 0.0048 1.0000
11.500 1.3816 0.06471 0.05663 -0.0693 0.0047 1.0000
11.750 1.3767 0.06867 0.06079 -0.0695 0.0048 1.0000
12.000 1.3720 0.07267 0.06497 -0.0696 0.0048 1.0000
12.250 1.3685 0.07656 0.06904 -0.0696 0.0048 1.0000
12.500 1.3660 0.08038 0.07305 -0.0695 0.0048 1.0000
12.750 1.3639 0.08435 0.07749 -0.0692 0.0048 1.0000
13.000 1.3617 0.08846 0.08182 -0.0693 0.0048 1.0000
13.250 1.3581 0.09295 0.08654 -0.0698 0.0048 1.0000
13.500 1.3530 0.09787 0.09170 -0.0707 0.0049 1.0000
13.750 1.3463 0.10327 0.09735 -0.0723 0.0049 1.0000
14.000 1.3383 0.10904 0.10336 -0.0744 0.0050 1.0000
14.250 1.3291 0.11527 0.10981 -0.0771 0.0050 1.0000
14.500 1.3194 0.12185 0.11662 -0.0802 0.0050 1.0000
14.750 1.3093 0.12878 0.12375 -0.0838 0.0050 1.0000
15.000 1.2991 0.13604 0.13120 -0.0879 0.0051 1.0000
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Polar data table (+)
Polar graphs
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