EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il) Reynolds number: 50,000 Max Cl/Cd: 34.87 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ec863914-il-50000.txt Download as CSV file: xf-ec863914-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER EC 86(-3)-914 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4542 0.12214 0.11581 -0.0360 1.0000 0.0984
-9.500 -0.4571 0.11777 0.11149 -0.0359 1.0000 0.0939
-9.250 -0.4879 0.10916 0.10303 -0.0403 1.0000 0.0862
-9.000 -0.4914 0.10536 0.09929 -0.0399 1.0000 0.0843
-8.750 -0.5042 0.10026 0.09429 -0.0406 1.0000 0.0820
-8.250 -0.6394 0.07938 0.07338 -0.0528 1.0000 0.0743
-8.000 -0.6475 0.07483 0.06881 -0.0533 1.0000 0.0735
-7.750 -0.6553 0.07017 0.06403 -0.0545 1.0000 0.0726
-7.500 -0.6614 0.06466 0.05829 -0.0565 1.0000 0.0715
-7.250 -0.6594 0.05916 0.05241 -0.0590 1.0000 0.0702
-7.000 -0.6485 0.05356 0.04627 -0.0620 1.0000 0.0690
-6.750 -0.6295 0.04885 0.04095 -0.0644 1.0000 0.0681
-6.500 -0.6067 0.04523 0.03681 -0.0658 1.0000 0.0680
-6.250 -0.5830 0.04244 0.03361 -0.0662 1.0000 0.0687
-6.000 -0.5599 0.04030 0.03115 -0.0658 1.0000 0.0700
-5.750 -0.5372 0.03862 0.02919 -0.0650 1.0000 0.0728
-5.500 -0.5157 0.03709 0.02760 -0.0640 1.0000 0.0767
-5.250 -0.4927 0.03578 0.02627 -0.0636 1.0000 0.0840
-5.000 -0.4675 0.03435 0.02482 -0.0637 1.0000 0.0954
-4.750 -0.4355 0.03250 0.02349 -0.0657 1.0000 0.1320
-4.500 -0.3737 0.03252 0.02404 -0.0764 1.0000 0.3453
-4.250 -0.3538 0.03305 0.02476 -0.0751 1.0000 0.3914
-4.000 -0.3323 0.03292 0.02457 -0.0741 1.0000 0.4123
-3.750 -0.3121 0.03292 0.02459 -0.0727 1.0000 0.4400
-3.500 -0.2898 0.03282 0.02442 -0.0720 1.0000 0.4653
-3.250 -0.2734 0.03298 0.02466 -0.0696 1.0000 0.4907
-3.000 -0.2570 0.03312 0.02487 -0.0673 1.0000 0.5110
-2.750 -0.2401 0.03328 0.02506 -0.0651 1.0000 0.5286
-2.500 -0.2226 0.03351 0.02529 -0.0632 1.0000 0.5477
-2.250 -0.2086 0.03394 0.02576 -0.0603 1.0000 0.5679
-2.000 -0.1985 0.03457 0.02642 -0.0564 1.0000 0.5888
-1.750 -0.1880 0.03524 0.02708 -0.0526 1.0000 0.6137
-1.500 -0.1788 0.03595 0.02779 -0.0485 1.0000 0.6434
-1.250 -0.1695 0.03667 0.02849 -0.0445 1.0000 0.6818
-1.000 -0.1690 0.03724 0.02906 -0.0383 1.0000 0.7167
-0.750 -0.1691 0.03755 0.02935 -0.0322 1.0000 0.7573
-0.500 -0.1714 0.03759 0.02935 -0.0257 1.0000 0.7980
-0.250 -0.1755 0.03733 0.02903 -0.0191 1.0000 0.8364
0.000 -0.1797 0.03679 0.02839 -0.0128 1.0000 0.8725
0.250 -0.1805 0.03615 0.02766 -0.0077 1.0000 0.9083
0.500 -0.1777 0.03535 0.02679 -0.0036 1.0000 0.9416
0.750 -0.1525 0.03494 0.02629 -0.0046 1.0000 0.9739
1.000 -0.1255 0.03438 0.02568 -0.0072 1.0000 1.0000
1.250 -0.1078 0.03471 0.02589 -0.0083 1.0000 1.0000
1.500 -0.0868 0.03530 0.02634 -0.0099 1.0000 1.0000
1.750 -0.0642 0.03608 0.02703 -0.0119 1.0000 1.0000
2.000 -0.0407 0.03702 0.02788 -0.0140 1.0000 1.0000
2.250 -0.0170 0.03809 0.02887 -0.0162 1.0000 1.0000
2.500 0.0069 0.03929 0.03002 -0.0185 1.0000 1.0000
2.750 0.0438 0.04147 0.03213 -0.0233 0.9948 1.0000
3.000 0.1695 0.04566 0.03610 -0.0408 0.9130 1.0000
3.250 0.2204 0.04668 0.03707 -0.0459 0.8858 1.0000
3.500 0.2753 0.04767 0.03804 -0.0515 0.8632 1.0000
3.750 0.3145 0.04811 0.03849 -0.0545 0.8396 1.0000
4.000 0.3610 0.04855 0.03896 -0.0583 0.8179 1.0000
4.250 0.4114 0.04876 0.03920 -0.0624 0.7969 1.0000
4.500 0.4550 0.04880 0.03930 -0.0652 0.7749 1.0000
4.750 0.5083 0.04837 0.03896 -0.0688 0.7548 1.0000
5.000 0.5513 0.04797 0.03865 -0.0709 0.7329 1.0000
5.250 0.6029 0.04701 0.03784 -0.0735 0.7129 1.0000
5.500 0.6631 0.04525 0.03621 -0.0763 0.6956 1.0000
5.750 0.7013 0.04447 0.03560 -0.0771 0.6719 1.0000
6.000 0.7627 0.04180 0.03310 -0.0790 0.6550 1.0000
6.250 0.8353 0.03815 0.02966 -0.0817 0.6387 1.0000
6.500 0.8976 0.03556 0.02722 -0.0839 0.6141 1.0000
6.750 0.9785 0.03261 0.02435 -0.0886 0.5837 1.0000
7.000 1.0514 0.03144 0.02308 -0.0937 0.5478 1.0000
7.250 1.0987 0.03201 0.02361 -0.0966 0.5163 1.0000
7.500 1.1477 0.03291 0.02449 -0.1000 0.4892 1.0000
7.750 1.1800 0.03427 0.02595 -0.1012 0.4679 1.0000
8.000 1.2211 0.03562 0.02736 -0.1038 0.4495 1.0000
8.250 1.2580 0.03711 0.02894 -0.1058 0.4335 1.0000
8.500 1.2831 0.03887 0.03092 -0.1062 0.4202 1.0000
8.750 1.3031 0.04089 0.03329 -0.1059 0.4091 1.0000
9.000 1.3268 0.04287 0.03551 -0.1061 0.3982 1.0000
9.250 1.3588 0.04475 0.03758 -0.1075 0.3874 1.0000
9.500 1.3658 0.04722 0.04043 -0.1055 0.3788 1.0000
9.750 1.3799 0.04968 0.04318 -0.1046 0.3701 1.0000
10.000 1.4144 0.05158 0.04529 -0.1060 0.3591 1.0000
10.250 1.3895 0.05520 0.04935 -0.1005 0.3536 1.0000
10.500 1.4101 0.05721 0.05161 -0.1001 0.3419 1.0000
10.750 1.4269 0.05883 0.05346 -0.0989 0.3279 1.0000
11.000 1.3891 0.06334 0.05829 -0.0929 0.3247 1.0000
11.250 1.3320 0.07027 0.06542 -0.0873 0.3256 1.0000
11.500 1.2501 0.08146 0.07664 -0.0841 0.3294 1.0000
11.750 1.3173 0.07708 0.07263 -0.0833 0.3043 1.0000
12.000 1.2841 0.08416 0.07982 -0.0819 0.3005 1.0000
12.250 1.3713 0.05710 0.05137 -0.0719 0.1721 1.0000
12.500 1.3436 0.06134 0.05574 -0.0690 0.1490 1.0000
12.750 1.3194 0.06614 0.06045 -0.0674 0.1268 1.0000
13.000 1.3007 0.07122 0.06543 -0.0668 0.1094 1.0000
13.250 1.2872 0.07638 0.07049 -0.0670 0.0966 1.0000
13.500 1.2780 0.08150 0.07560 -0.0675 0.0869 1.0000
13.750 1.2737 0.08609 0.08008 -0.0679 0.0796 1.0000
14.000 1.2732 0.09073 0.08495 -0.0683 0.0740 1.0000
14.250 1.2824 0.09398 0.08806 -0.0679 0.0684 1.0000
14.500 1.2783 0.09943 0.09390 -0.0692 0.0661 1.0000
14.750 1.2719 0.10521 0.10000 -0.0711 0.0642 1.0000
15.000 1.2632 0.11149 0.10656 -0.0737 0.0628 1.0000
15.250 1.2506 0.11864 0.11399 -0.0773 0.0622 1.0000
15.500 1.2282 0.12823 0.12393 -0.0831 0.0634 1.0000
15.750 1.1974 0.14049 0.13650 -0.0913 0.0662 1.0000
16.000 1.1737 0.15209 0.14825 -0.0991 0.0681 1.0000
16.250 1.1559 0.16308 0.15929 -0.1063 0.0692 1.0000
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