EPPLER 562 AIRFOIL (e562-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 562 AIRFOIL (e562-il) Reynolds number: 50,000 Max Cl/Cd: 33.94 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e562-il-50000-n5.txt Download as CSV file: xf-e562-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 562 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4317 0.10047 0.09317 -0.0532 1.0000 0.0608
-11.000 -0.4565 0.09185 0.08462 -0.0568 1.0000 0.0608
-10.750 -0.4866 0.08313 0.07595 -0.0608 1.0000 0.0604
-10.500 -0.5184 0.07525 0.06803 -0.0644 1.0000 0.0600
-10.250 -0.5472 0.06891 0.06164 -0.0669 1.0000 0.0596
-10.000 -0.5741 0.06385 0.05652 -0.0681 1.0000 0.0594
-9.750 -0.6000 0.05993 0.05254 -0.0680 1.0000 0.0592
-9.500 -0.6229 0.05618 0.04868 -0.0682 1.0000 0.0595
-9.250 -0.6375 0.05260 0.04492 -0.0683 1.0000 0.0602
-9.000 -0.6450 0.04944 0.04147 -0.0679 1.0000 0.0613
-8.750 -0.6415 0.04747 0.03954 -0.0665 1.0000 0.0631
-8.500 -0.6372 0.04558 0.03763 -0.0654 1.0000 0.0653
-8.250 -0.6319 0.04352 0.03542 -0.0647 1.0000 0.0686
-8.000 -0.6244 0.04130 0.03290 -0.0641 1.0000 0.0726
-7.750 -0.6145 0.03982 0.03149 -0.0632 1.0000 0.0767
-7.500 -0.6027 0.03809 0.02960 -0.0626 1.0000 0.0822
-7.250 -0.5897 0.03650 0.02801 -0.0623 1.0000 0.0890
-7.000 -0.5745 0.03489 0.02628 -0.0623 1.0000 0.0989
-6.750 -0.5545 0.03330 0.02473 -0.0633 0.9989 0.1132
-6.500 -0.5164 0.03172 0.02321 -0.0679 0.9918 0.1412
-6.250 -0.4772 0.03082 0.02243 -0.0722 0.9843 0.1786
-6.000 -0.4394 0.03044 0.02202 -0.0756 0.9757 0.2163
-5.750 -0.4025 0.03038 0.02187 -0.0782 0.9668 0.2474
-5.500 -0.3657 0.03050 0.02190 -0.0802 0.9580 0.2730
-5.250 -0.3290 0.03050 0.02175 -0.0823 0.9489 0.2957
-5.000 -0.2962 0.03049 0.02162 -0.0834 0.9387 0.3137
-4.750 -0.2615 0.03036 0.02135 -0.0849 0.9292 0.3305
-4.500 -0.2240 0.03020 0.02102 -0.0868 0.9206 0.3468
-4.250 -0.1923 0.02998 0.02065 -0.0878 0.9097 0.3616
-4.000 -0.1568 0.02978 0.02029 -0.0894 0.9006 0.3768
-3.750 -0.1207 0.02950 0.01984 -0.0911 0.8913 0.3916
-3.500 -0.0890 0.02927 0.01948 -0.0919 0.8806 0.4044
-3.250 -0.0492 0.02896 0.01908 -0.0939 0.8734 0.4167
-3.000 -0.0193 0.02868 0.01868 -0.0945 0.8618 0.4281
-2.750 0.0165 0.02831 0.01813 -0.0960 0.8526 0.4412
-2.500 0.0527 0.02796 0.01769 -0.0974 0.8439 0.4528
-2.250 0.0840 0.02772 0.01737 -0.0979 0.8332 0.4637
-2.000 0.1256 0.02728 0.01680 -0.1002 0.8261 0.4769
-1.750 0.1563 0.02707 0.01648 -0.1009 0.8144 0.4893
-1.500 0.1918 0.02681 0.01617 -0.1019 0.8054 0.5004
-1.250 0.2268 0.02654 0.01583 -0.1030 0.7956 0.5124
-1.000 0.2581 0.02637 0.01557 -0.1036 0.7843 0.5251
-0.750 0.2988 0.02600 0.01510 -0.1055 0.7767 0.5386
-0.500 0.3256 0.02596 0.01505 -0.1052 0.7643 0.5496
-0.250 0.3567 0.02584 0.01489 -0.1056 0.7533 0.5621
0.000 0.3946 0.02556 0.01454 -0.1070 0.7447 0.5761
0.250 0.4219 0.02558 0.01452 -0.1069 0.7323 0.5896
0.500 0.4513 0.02554 0.01447 -0.1069 0.7214 0.6026
0.750 0.4861 0.02535 0.01425 -0.1077 0.7122 0.6172
1.000 0.5109 0.02544 0.01437 -0.1071 0.7000 0.6311
1.250 0.5392 0.02546 0.01439 -0.1070 0.6893 0.6464
1.500 0.5716 0.02535 0.01428 -0.1074 0.6799 0.6631
1.750 0.5946 0.02552 0.01449 -0.1065 0.6680 0.6797
2.000 0.6217 0.02557 0.01457 -0.1061 0.6580 0.6983
2.250 0.6500 0.02557 0.01461 -0.1058 0.6482 0.7192
2.500 0.6704 0.02575 0.01490 -0.1044 0.6373 0.7406
2.750 0.6977 0.02570 0.01489 -0.1038 0.6286 0.7669
3.000 0.7159 0.02585 0.01518 -0.1018 0.6180 0.7969
3.250 0.7353 0.02590 0.01536 -0.0999 0.6087 0.8378
3.500 0.7621 0.02577 0.01533 -0.0992 0.5996 0.9164
3.750 0.7921 0.02616 0.01571 -0.1004 0.5887 1.0000
4.000 0.8284 0.02642 0.01583 -0.1021 0.5804 1.0000
4.250 0.8526 0.02701 0.01640 -0.1021 0.5698 1.0000
4.500 0.8806 0.02748 0.01684 -0.1024 0.5606 1.0000
4.750 0.9091 0.02791 0.01723 -0.1027 0.5516 1.0000
5.000 0.9318 0.02855 0.01787 -0.1023 0.5420 1.0000
5.250 0.9629 0.02888 0.01817 -0.1028 0.5340 1.0000
5.500 0.9815 0.02966 0.01902 -0.1017 0.5240 1.0000
5.750 1.0148 0.02990 0.01921 -0.1024 0.5166 1.0000
6.000 1.0294 0.03084 0.02028 -0.1009 0.5065 1.0000
6.250 1.0584 0.03124 0.02066 -0.1010 0.4988 1.0000
6.500 1.0754 0.03210 0.02163 -0.0997 0.4893 1.0000
6.750 1.1004 0.03266 0.02222 -0.0993 0.4813 1.0000
7.000 1.1194 0.03343 0.02310 -0.0982 0.4723 1.0000
7.250 1.1402 0.03417 0.02391 -0.0973 0.4640 1.0000
7.500 1.1611 0.03485 0.02468 -0.0964 0.4554 1.0000
7.750 1.1774 0.03577 0.02573 -0.0950 0.4468 1.0000
8.000 1.2008 0.03633 0.02636 -0.0943 0.4385 1.0000
8.250 1.2113 0.03748 0.02765 -0.0922 0.4295 1.0000
8.500 1.2386 0.03784 0.02806 -0.0920 0.4215 1.0000
8.750 1.2416 0.03929 0.02971 -0.0891 0.4121 1.0000
9.000 1.2756 0.03928 0.02972 -0.0894 0.4042 1.0000
9.250 1.2666 0.04118 0.03183 -0.0852 0.3947 1.0000
9.500 1.2903 0.04156 0.03228 -0.0844 0.3863 1.0000
9.750 1.2891 0.04313 0.03402 -0.0812 0.3771 1.0000
10.000 1.2989 0.04419 0.03520 -0.0792 0.3683 1.0000
10.250 1.3117 0.04503 0.03615 -0.0774 0.3591 1.0000
10.500 1.3030 0.04725 0.03853 -0.0742 0.3501 1.0000
10.750 1.3350 0.04683 0.03813 -0.0738 0.3408 1.0000
11.000 1.3052 0.05071 0.04225 -0.0699 0.3318 1.0000
11.250 1.3186 0.05153 0.04315 -0.0684 0.3226 1.0000
11.500 1.3125 0.05399 0.04575 -0.0665 0.3131 1.0000
11.750 1.2963 0.05768 0.04959 -0.0648 0.3039 1.0000
12.000 1.3260 0.05682 0.04877 -0.0637 0.2941 1.0000
12.250 1.2802 0.06418 0.05635 -0.0630 0.2848 1.0000
12.500 1.2826 0.06640 0.05866 -0.0623 0.2753 1.0000
12.750 1.2954 0.06727 0.05961 -0.0613 0.2653 1.0000
13.000 1.2451 0.07706 0.06956 -0.0632 0.2554 1.0000
13.250 1.2610 0.07749 0.07007 -0.0622 0.2459 1.0000
13.500 1.2602 0.08049 0.07316 -0.0623 0.2360 1.0000
13.750 1.2132 0.09135 0.08415 -0.0659 0.2256 1.0000
14.000 1.2401 0.08980 0.08266 -0.0641 0.2167 1.0000
14.250 1.2297 0.09478 0.08774 -0.0654 0.2069 1.0000
14.500 1.1886 0.10586 0.09892 -0.0699 0.1968 1.0000
14.750 1.2326 0.10075 0.09386 -0.0663 0.1884 1.0000
15.000 1.1939 0.11176 0.10498 -0.0711 0.1792 1.0000
15.250 1.1758 0.11914 0.11242 -0.0743 0.1703 1.0000
15.500 1.2303 0.11135 0.10466 -0.0691 0.1618 1.0000
15.750 1.1548 0.13134 0.12474 -0.0796 0.1535 1.0000
16.000 1.2058 0.12364 0.11709 -0.0744 0.1461 1.0000
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Polar data table (+)
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