GOE 426 AIRFOIL (goe426-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 426 AIRFOIL (goe426-il) Reynolds number: 100,000 Max Cl/Cd: 52.14 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe426-il-100000-n5.txt Download as CSV file: xf-goe426-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 426 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2623 0.10653 0.10162 -0.0459 1.0000 0.0792
-9.500 -0.2880 0.10502 0.10028 -0.0480 1.0000 0.0812
-9.250 -0.2924 0.10065 0.09596 -0.0564 0.9865 0.0817
-9.000 -0.2627 0.09603 0.09132 -0.0549 0.9827 0.0828
-8.750 -0.2389 0.09248 0.08774 -0.0565 0.9744 0.0843
-8.500 -0.2192 0.08869 0.08394 -0.0603 0.9646 0.0859
-8.250 -0.2428 0.07284 0.06796 -0.0838 0.9389 0.0599
-8.000 -0.2252 0.06878 0.06389 -0.0872 0.9278 0.0605
-7.750 -0.2062 0.06602 0.06108 -0.0884 0.9143 0.0585
-7.500 -0.1959 0.06159 0.05658 -0.0924 0.8984 0.0569
-7.000 -0.2087 0.04602 0.03985 -0.1035 0.8624 0.0505
-6.750 -0.1940 0.04303 0.03661 -0.1040 0.8488 0.0502
-6.500 -0.1784 0.04013 0.03339 -0.1043 0.8355 0.0501
-6.250 -0.1609 0.03744 0.03029 -0.1045 0.8230 0.0502
-6.000 -0.1417 0.03496 0.02732 -0.1046 0.8114 0.0509
-5.750 -0.1201 0.03300 0.02517 -0.1045 0.8000 0.0517
-5.500 -0.0980 0.03123 0.02312 -0.1043 0.7883 0.0521
-5.250 -0.0744 0.02943 0.02093 -0.1041 0.7781 0.0521
-5.000 -0.0500 0.02789 0.01905 -0.1038 0.7677 0.0522
-4.750 -0.0253 0.02657 0.01745 -0.1035 0.7569 0.0525
-4.500 0.0006 0.02538 0.01598 -0.1032 0.7476 0.0529
-4.250 0.0260 0.02435 0.01474 -0.1028 0.7370 0.0535
-4.000 0.0521 0.02345 0.01365 -0.1025 0.7278 0.0544
-3.750 0.0784 0.02271 0.01274 -0.1022 0.7186 0.0560
-3.500 0.1046 0.02203 0.01189 -0.1018 0.7093 0.0577
-3.250 0.1312 0.02135 0.01103 -0.1014 0.7008 0.0587
-3.000 0.1572 0.02076 0.01033 -0.1009 0.6918 0.0595
-2.750 0.1831 0.02013 0.00965 -0.1005 0.6841 0.0605
-2.500 0.2082 0.01959 0.00913 -0.1000 0.6759 0.0619
-2.250 0.2339 0.01917 0.00867 -0.0996 0.6682 0.0636
-2.000 0.2596 0.01886 0.00830 -0.0992 0.6607 0.0662
-1.750 0.2857 0.01861 0.00795 -0.0989 0.6533 0.0701
-1.500 0.3119 0.01831 0.00762 -0.0986 0.6470 0.0745
-1.250 0.3380 0.01811 0.00737 -0.0983 0.6395 0.0796
-1.000 0.3649 0.01787 0.00708 -0.0980 0.6337 0.0887
-0.750 0.3908 0.01758 0.00690 -0.0977 0.6267 0.1177
-0.500 0.4126 0.01626 0.00689 -0.0974 0.6207 0.4593
-0.250 0.4347 0.01591 0.00702 -0.0958 0.6155 0.6305
0.000 0.4549 0.01574 0.00718 -0.0937 0.6089 0.7374
0.250 0.4771 0.01551 0.00715 -0.0916 0.6035 0.8382
0.500 0.5316 0.01534 0.00698 -0.0964 0.5972 1.0000
0.750 0.5571 0.01552 0.00701 -0.0962 0.5911 1.0000
1.000 0.5839 0.01567 0.00697 -0.0961 0.5860 1.0000
1.250 0.6097 0.01588 0.00706 -0.0959 0.5802 1.0000
1.500 0.6357 0.01609 0.00716 -0.0957 0.5745 1.0000
1.750 0.6628 0.01627 0.00719 -0.0956 0.5698 1.0000
2.000 0.6886 0.01651 0.00735 -0.0953 0.5642 1.0000
2.250 0.7145 0.01675 0.00752 -0.0951 0.5586 1.0000
2.500 0.7416 0.01696 0.00761 -0.0950 0.5540 1.0000
2.750 0.7674 0.01723 0.00783 -0.0947 0.5488 1.0000
3.000 0.7928 0.01750 0.00808 -0.0944 0.5432 1.0000
3.250 0.8196 0.01773 0.00823 -0.0943 0.5384 1.0000
3.500 0.8458 0.01801 0.00846 -0.0941 0.5337 1.0000
3.750 0.8703 0.01833 0.00881 -0.0937 0.5280 1.0000
4.000 0.8965 0.01860 0.00903 -0.0934 0.5231 1.0000
4.250 0.9238 0.01886 0.00923 -0.0934 0.5188 1.0000
4.500 0.9467 0.01924 0.00969 -0.0928 0.5127 1.0000
4.750 0.9721 0.01954 0.01000 -0.0924 0.5077 1.0000
5.000 0.9995 0.01981 0.01022 -0.0924 0.5035 1.0000
5.250 1.0219 0.02022 0.01073 -0.0917 0.4976 1.0000
5.500 1.0461 0.02057 0.01112 -0.0912 0.4921 1.0000
5.750 1.0728 0.02086 0.01140 -0.0911 0.4878 1.0000
6.000 1.0954 0.02129 0.01193 -0.0904 0.4825 1.0000
6.250 1.1181 0.02170 0.01243 -0.0898 0.4767 1.0000
6.500 1.1439 0.02200 0.01274 -0.0895 0.4721 1.0000
6.750 1.1665 0.02244 0.01327 -0.0888 0.4669 1.0000
7.000 1.1876 0.02292 0.01388 -0.0880 0.4612 1.0000
7.250 1.2125 0.02326 0.01426 -0.0876 0.4565 1.0000
7.500 1.2352 0.02369 0.01479 -0.0870 0.4515 1.0000
7.750 1.2541 0.02424 0.01550 -0.0858 0.4455 1.0000
8.000 1.2780 0.02461 0.01594 -0.0853 0.4409 1.0000
8.250 1.3004 0.02505 0.01649 -0.0846 0.4362 1.0000
8.500 1.3167 0.02566 0.01727 -0.0831 0.4295 1.0000
8.750 1.3409 0.02587 0.01752 -0.0826 0.4239 1.0000
9.000 1.3551 0.02648 0.01832 -0.0808 0.4167 1.0000
9.250 1.3748 0.02676 0.01870 -0.0796 0.4096 1.0000
9.500 1.3891 0.02728 0.01936 -0.0777 0.4021 1.0000
9.750 1.4058 0.02756 0.01972 -0.0761 0.3939 1.0000
10.000 1.4139 0.02811 0.02041 -0.0734 0.3841 1.0000
10.250 1.4221 0.02842 0.02076 -0.0705 0.3732 1.0000
10.500 1.4263 0.02888 0.02124 -0.0672 0.3604 1.0000
10.750 1.4256 0.02968 0.02206 -0.0637 0.3461 1.0000
11.000 1.4216 0.03087 0.02329 -0.0603 0.3302 1.0000
11.250 1.4170 0.03238 0.02484 -0.0573 0.3146 1.0000
11.500 1.4116 0.03423 0.02672 -0.0548 0.2989 1.0000
11.750 1.4059 0.03638 0.02892 -0.0528 0.2833 1.0000
12.000 1.3995 0.03885 0.03145 -0.0511 0.2674 1.0000
12.250 1.3918 0.04167 0.03433 -0.0498 0.2505 1.0000
12.500 1.3826 0.04485 0.03753 -0.0488 0.2319 1.0000
12.750 1.3706 0.04848 0.04113 -0.0480 0.2117 1.0000
13.000 1.3559 0.05261 0.04520 -0.0475 0.1891 1.0000
13.250 1.3386 0.05727 0.04976 -0.0474 0.1678 1.0000
13.500 1.3215 0.06220 0.05460 -0.0476 0.1487 1.0000
13.750 1.3049 0.06728 0.05962 -0.0481 0.1330 1.0000
14.000 1.2895 0.07246 0.06476 -0.0488 0.1189 1.0000
14.250 1.2756 0.07762 0.06990 -0.0497 0.1057 1.0000
14.500 1.2636 0.08268 0.07497 -0.0507 0.0927 1.0000
14.750 1.2523 0.08780 0.08009 -0.0518 0.0800 1.0000
15.000 1.2408 0.09306 0.08533 -0.0531 0.0692 1.0000
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Polar data table (+)
Polar graphs
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