EPPLER 855 AIRFOIL (e855-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 855 AIRFOIL (e855-il) Reynolds number: 50,000 Max Cl/Cd: 23.02 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e855-il-50000-n5.txt Download as CSV file: xf-e855-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 855 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3743 0.10243 0.09561 -0.0563 1.0000 0.0461
-10.500 -0.3866 0.09655 0.08986 -0.0582 1.0000 0.0459
-10.250 -0.4033 0.09010 0.08351 -0.0605 1.0000 0.0455
-10.000 -0.4245 0.08376 0.07724 -0.0629 1.0000 0.0445
-9.750 -0.4555 0.07714 0.07068 -0.0654 1.0000 0.0433
-9.500 -0.5089 0.07014 0.06363 -0.0676 1.0000 0.0409
-9.250 -0.5614 0.06625 0.05965 -0.0661 1.0000 0.0396
-9.000 -0.5871 0.06348 0.05679 -0.0640 1.0000 0.0395
-8.750 -0.6065 0.06083 0.05400 -0.0618 1.0000 0.0394
-8.500 -0.6183 0.05834 0.05141 -0.0598 1.0000 0.0398
-8.250 -0.5952 0.05486 0.04774 -0.0642 0.9907 0.0418
-8.000 -0.5733 0.05113 0.04362 -0.0681 0.9809 0.0443
-7.750 -0.5503 0.04717 0.03904 -0.0714 0.9712 0.0471
-7.500 -0.5250 0.04375 0.03513 -0.0734 0.9617 0.0497
-7.250 -0.4984 0.04174 0.03303 -0.0750 0.9518 0.0543
-7.000 -0.4694 0.03943 0.03018 -0.0763 0.9425 0.0599
-6.750 -0.4377 0.03760 0.02838 -0.0781 0.9345 0.0672
-6.500 -0.4113 0.03594 0.02654 -0.0784 0.9242 0.0755
-6.250 -0.3822 0.03446 0.02489 -0.0792 0.9149 0.0871
-6.000 -0.3514 0.03293 0.02335 -0.0807 0.9065 0.1024
-5.750 -0.3265 0.03154 0.02196 -0.0813 0.8958 0.1205
-5.500 -0.2964 0.02994 0.02044 -0.0830 0.8876 0.1492
-5.250 -0.2688 0.02828 0.01902 -0.0845 0.8782 0.1931
-5.000 -0.2429 0.02686 0.01822 -0.0856 0.8686 0.2762
-4.750 -0.2094 0.02668 0.01837 -0.0864 0.8613 0.3833
-4.500 -0.1825 0.02700 0.01856 -0.0858 0.8508 0.4367
-4.250 -0.1440 0.02723 0.01852 -0.0870 0.8449 0.4790
-4.000 -0.1199 0.02756 0.01868 -0.0857 0.8339 0.5049
-3.750 -0.0891 0.02779 0.01875 -0.0854 0.8260 0.5297
-3.500 -0.0597 0.02794 0.01873 -0.0851 0.8176 0.5525
-3.250 -0.0321 0.02799 0.01860 -0.0847 0.8087 0.5722
-3.000 -0.0003 0.02791 0.01832 -0.0849 0.8014 0.5883
-2.750 0.0252 0.02788 0.01813 -0.0844 0.7922 0.6009
-2.500 0.0585 0.02766 0.01774 -0.0851 0.7856 0.6119
-2.250 0.0838 0.02758 0.01747 -0.0849 0.7763 0.6220
-2.000 0.1190 0.02730 0.01698 -0.0864 0.7700 0.6326
-1.750 0.1418 0.02732 0.01690 -0.0856 0.7607 0.6405
-1.500 0.1769 0.02708 0.01645 -0.0872 0.7546 0.6506
-1.250 0.1990 0.02716 0.01644 -0.0863 0.7456 0.6583
-1.000 0.2330 0.02698 0.01609 -0.0876 0.7395 0.6677
-0.750 0.2553 0.02711 0.01614 -0.0870 0.7311 0.6761
-0.500 0.2867 0.02703 0.01595 -0.0878 0.7249 0.6851
-0.250 0.3111 0.02716 0.01598 -0.0876 0.7172 0.6945
0.000 0.3384 0.02719 0.01596 -0.0876 0.7106 0.7033
0.250 0.3674 0.02724 0.01592 -0.0881 0.7045 0.7135
0.500 0.3882 0.02749 0.01615 -0.0873 0.6968 0.7231
0.750 0.4218 0.02739 0.01599 -0.0882 0.6923 0.7337
1.000 0.4367 0.02787 0.01649 -0.0867 0.6838 0.7447
1.250 0.4664 0.02791 0.01648 -0.0870 0.6786 0.7569
1.500 0.4855 0.02825 0.01686 -0.0859 0.6719 0.7692
1.750 0.5070 0.02852 0.01716 -0.0851 0.6655 0.7829
2.000 0.5389 0.02846 0.01711 -0.0856 0.6615 0.7985
2.250 0.5466 0.02918 0.01794 -0.0830 0.6532 0.8161
2.500 0.5726 0.02927 0.01809 -0.0826 0.6484 0.8370
2.750 0.5940 0.02956 0.01846 -0.0818 0.6430 0.8633
3.000 0.6132 0.03013 0.01919 -0.0811 0.6360 0.9031
3.250 0.6605 0.03011 0.01920 -0.0851 0.6318 1.0000
3.500 0.6733 0.03125 0.02031 -0.0844 0.6243 1.0000
3.750 0.7000 0.03186 0.02088 -0.0852 0.6189 1.0000
4.000 0.7374 0.03204 0.02100 -0.0871 0.6155 1.0000
4.250 0.7359 0.03377 0.02275 -0.0843 0.6065 1.0000
4.500 0.7660 0.03420 0.02318 -0.0851 0.6022 1.0000
4.750 0.7783 0.03542 0.02441 -0.0838 0.5958 1.0000
5.000 0.7891 0.03664 0.02566 -0.0823 0.5890 1.0000
5.250 0.8246 0.03684 0.02588 -0.0835 0.5856 1.0000
5.750 0.8381 0.03977 0.02891 -0.0796 0.5716 1.0000
6.250 0.8517 0.04301 0.03226 -0.0762 0.5573 1.0000
6.500 0.8897 0.04286 0.03220 -0.0772 0.5543 1.0000
6.750 0.8657 0.04649 0.03588 -0.0733 0.5424 1.0000
7.000 0.9029 0.04622 0.03571 -0.0739 0.5394 1.0000
7.250 0.8820 0.05001 0.03955 -0.0710 0.5270 1.0000
7.500 0.9199 0.04950 0.03915 -0.0713 0.5241 1.0000
7.750 0.9015 0.05342 0.04314 -0.0691 0.5113 1.0000
8.000 0.9406 0.05257 0.04243 -0.0692 0.5086 1.0000
8.250 0.9245 0.05649 0.04642 -0.0675 0.4955 1.0000
8.500 0.9654 0.05526 0.04534 -0.0672 0.4929 1.0000
8.750 0.9517 0.05903 0.04919 -0.0658 0.4795 1.0000
9.250 0.9826 0.06101 0.05146 -0.0640 0.4633 1.0000
9.750 0.9736 0.06688 0.05753 -0.0620 0.4378 1.0000
10.000 1.0140 0.06490 0.05575 -0.0609 0.4333 1.0000
10.250 1.0113 0.06758 0.05856 -0.0600 0.4198 1.0000
10.500 1.0121 0.06989 0.06100 -0.0591 0.4068 1.0000
11.000 1.0585 0.06878 0.06026 -0.0565 0.3886 1.0000
11.250 1.0609 0.07076 0.06237 -0.0556 0.3747 1.0000
11.750 1.0724 0.07388 0.06582 -0.0539 0.3470 1.0000
12.250 1.0928 0.07572 0.06796 -0.0519 0.3186 1.0000
12.500 1.1066 0.07609 0.06849 -0.0509 0.3036 1.0000
12.750 1.1242 0.07588 0.06841 -0.0496 0.2876 1.0000
13.000 1.1424 0.07556 0.06816 -0.0482 0.2697 1.0000
13.250 1.1486 0.07720 0.06987 -0.0475 0.2502 1.0000
13.500 1.1621 0.07767 0.07026 -0.0463 0.2300 1.0000
13.750 1.1688 0.07928 0.07177 -0.0456 0.2112 1.0000
14.000 1.1687 0.08214 0.07458 -0.0454 0.1940 1.0000
14.250 1.1689 0.08505 0.07744 -0.0453 0.1785 1.0000
14.500 1.1683 0.08816 0.08050 -0.0453 0.1645 1.0000
14.750 1.1680 0.09133 0.08364 -0.0455 0.1519 1.0000
15.000 1.1688 0.09437 0.08661 -0.0457 0.1406 1.0000
15.250 1.1683 0.09773 0.08999 -0.0462 0.1300 1.0000
15.500 1.1667 0.10150 0.09386 -0.0469 0.1206 1.0000
15.750 1.1679 0.10471 0.09711 -0.0475 0.1122 1.0000
16.000 1.1681 0.10817 0.10062 -0.0483 0.1042 1.0000
16.250 1.1673 0.11202 0.10460 -0.0492 0.0974 1.0000
16.500 1.1693 0.11517 0.10776 -0.0500 0.0907 1.0000
16.750 1.1659 0.11964 0.11240 -0.0516 0.0853 1.0000
17.000 1.1643 0.12373 0.11663 -0.0531 0.0801 1.0000
17.250 1.1664 0.12703 0.11993 -0.0541 0.0752 1.0000
17.500 1.1554 0.13340 0.12661 -0.0572 0.0718 1.0000
17.750 1.1506 0.13842 0.13177 -0.0596 0.0683 1.0000
18.000 1.1567 0.14088 0.13415 -0.0605 0.0642 1.0000
18.250 1.1371 0.14968 0.14327 -0.0655 0.0628 1.0000
18.500 1.1117 0.16053 0.15436 -0.0720 0.0622 1.0000
18.750 1.0757 0.17558 0.16953 -0.0811 0.0623 1.0000
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