EPPLER E851 AIRFOIL (e851-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: EPPLER E851 AIRFOIL (e851-il) Reynolds number: 100,000 Max Cl/Cd: 50.74 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e851-il-100000-n5.txt Download as CSV file: xf-e851-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E851 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4615 0.09223 0.08724 -0.0395 1.0000 0.0110
-8.750 -0.4671 0.08819 0.08329 -0.0404 1.0000 0.0107
-8.500 -0.4744 0.08415 0.07933 -0.0412 1.0000 0.0104
-8.250 -0.4842 0.08012 0.07539 -0.0419 1.0000 0.0102
-8.000 -0.4976 0.07604 0.07141 -0.0424 1.0000 0.0100
-7.750 -0.5165 0.07206 0.06752 -0.0428 1.0000 0.0098
-7.500 -0.5337 0.06756 0.06304 -0.0445 1.0000 0.0096
-7.250 -0.5470 0.06331 0.05871 -0.0449 1.0000 0.0094
-7.000 -0.5562 0.05900 0.05427 -0.0449 1.0000 0.0092
-6.750 -0.5597 0.05473 0.04982 -0.0447 1.0000 0.0089
-6.500 -0.5570 0.05064 0.04545 -0.0445 1.0000 0.0086
-6.250 -0.5361 0.04555 0.03990 -0.0478 0.9964 0.0084
-6.000 -0.5119 0.04104 0.03487 -0.0505 0.9931 0.0082
-5.750 -0.4877 0.03726 0.03057 -0.0522 0.9897 0.0081
-5.500 -0.4619 0.03344 0.02618 -0.0537 0.9868 0.0082
-5.250 -0.4343 0.03003 0.02220 -0.0548 0.9844 0.0083
-5.000 -0.4053 0.02715 0.01885 -0.0557 0.9825 0.0087
-4.750 -0.3763 0.02541 0.01685 -0.0568 0.9804 0.0107
-4.500 -0.3495 0.02426 0.01545 -0.0569 0.9775 0.0141
-4.250 -0.3209 0.02306 0.01385 -0.0570 0.9749 0.0173
-4.000 -0.2932 0.02098 0.01166 -0.0573 0.9728 0.0207
-3.750 -0.2625 0.01982 0.01042 -0.0582 0.9706 0.0384
-3.500 -0.2308 0.01838 0.00915 -0.0596 0.9689 0.0912
-3.250 -0.2055 0.01647 0.00845 -0.0608 0.9666 0.3445
-3.000 -0.1806 0.01617 0.00860 -0.0603 0.9630 0.5081
-2.750 -0.1525 0.01621 0.00862 -0.0603 0.9598 0.5669
-2.500 -0.1229 0.01631 0.00865 -0.0605 0.9571 0.6105
-2.250 -0.0975 0.01639 0.00871 -0.0599 0.9537 0.6448
-2.000 -0.0717 0.01640 0.00854 -0.0595 0.9497 0.6654
-1.750 -0.0422 0.01641 0.00844 -0.0600 0.9466 0.6787
-1.500 -0.0105 0.01644 0.00836 -0.0610 0.9440 0.6914
-1.250 0.0157 0.01645 0.00831 -0.0609 0.9401 0.7039
-1.000 0.0426 0.01648 0.00828 -0.0610 0.9360 0.7167
-0.750 0.0732 0.01651 0.00828 -0.0618 0.9329 0.7301
-0.500 0.1057 0.01654 0.00824 -0.0629 0.9305 0.7443
-0.250 0.1287 0.01658 0.00830 -0.0621 0.9252 0.7591
0.000 0.1574 0.01661 0.00835 -0.0624 0.9213 0.7759
0.250 0.1892 0.01662 0.00841 -0.0634 0.9183 0.7948
0.500 0.2131 0.01665 0.00851 -0.0627 0.9132 0.8164
0.750 0.2400 0.01665 0.00861 -0.0625 0.9085 0.8433
1.000 0.2725 0.01659 0.00867 -0.0634 0.9053 0.8793
1.250 0.3086 0.01654 0.00876 -0.0654 0.9006 0.9516
1.500 0.3410 0.01661 0.00884 -0.0668 0.8951 1.0000
1.750 0.3790 0.01666 0.00893 -0.0691 0.8917 1.0000
2.000 0.4048 0.01681 0.00922 -0.0690 0.8840 1.0000
2.250 0.4424 0.01680 0.00930 -0.0711 0.8795 1.0000
2.500 0.4709 0.01687 0.00946 -0.0713 0.8713 1.0000
2.750 0.5126 0.01665 0.00940 -0.0738 0.8658 1.0000
3.000 0.5446 0.01650 0.00940 -0.0742 0.8551 1.0000
3.250 0.5855 0.01601 0.00921 -0.0759 0.8418 1.0000
3.500 0.6243 0.01519 0.00859 -0.0764 0.8177 1.0000
3.750 0.6589 0.01449 0.00807 -0.0761 0.7853 1.0000
4.000 0.6820 0.01418 0.00790 -0.0741 0.7384 1.0000
4.250 0.7230 0.01425 0.00685 -0.0739 0.4756 1.0000
4.500 0.7270 0.01629 0.00760 -0.0699 0.2491 1.0000
4.750 0.7389 0.01817 0.00855 -0.0677 0.1033 1.0000
5.000 0.7562 0.01957 0.00972 -0.0659 0.0622 1.0000
5.250 0.7735 0.02100 0.01107 -0.0640 0.0370 1.0000
5.500 0.7914 0.02245 0.01256 -0.0622 0.0227 1.0000
5.750 0.8104 0.02410 0.01451 -0.0604 0.0163 1.0000
6.000 0.8311 0.02697 0.01752 -0.0590 0.0138 1.0000
6.250 0.8581 0.02923 0.02003 -0.0584 0.0123 1.0000
6.500 0.8831 0.03092 0.02203 -0.0577 0.0095 1.0000
6.750 0.9048 0.03258 0.02396 -0.0568 0.0075 1.0000
7.000 0.9243 0.03495 0.02666 -0.0555 0.0067 1.0000
7.250 0.9414 0.03812 0.03028 -0.0537 0.0065 1.0000
7.500 0.9545 0.04151 0.03413 -0.0515 0.0064 1.0000
7.750 0.9631 0.04512 0.03820 -0.0488 0.0063 1.0000
8.000 0.9681 0.04882 0.04234 -0.0459 0.0063 1.0000
8.250 0.9690 0.05266 0.04658 -0.0428 0.0063 1.0000
8.500 0.9661 0.05657 0.05085 -0.0397 0.0064 1.0000
8.750 0.9593 0.06052 0.05512 -0.0365 0.0065 1.0000
9.000 0.9469 0.06424 0.05908 -0.0330 0.0066 1.0000
9.250 0.9321 0.06818 0.06323 -0.0302 0.0067 1.0000
9.500 0.9154 0.07244 0.06767 -0.0284 0.0068 1.0000
9.750 0.8977 0.07718 0.07258 -0.0280 0.0069 1.0000
10.000 0.8789 0.08281 0.07835 -0.0293 0.0071 1.0000
10.250 0.8606 0.08973 0.08537 -0.0326 0.0073 1.0000
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Polar data table (+)
Polar graphs
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