GOE 526 AIRFOIL (goe526-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 526 AIRFOIL (goe526-il) Reynolds number: 200,000 Max Cl/Cd: 73.9 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe526-il-200000.txt Download as CSV file: xf-goe526-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 526 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3170 0.10317 0.09948 -0.0408 1.0000 0.0779
-9.500 -0.3681 0.10190 0.09837 -0.0418 1.0000 0.0791
-9.250 -0.4030 0.10060 0.09718 -0.0410 0.9990 0.0793
-9.000 -0.3759 0.09628 0.09285 -0.0392 0.9979 0.0801
-8.750 -0.3476 0.09331 0.08986 -0.0398 0.9953 0.0811
-8.500 -0.3241 0.09009 0.08663 -0.0428 0.9916 0.0829
-8.250 -0.3062 0.08623 0.08276 -0.0479 0.9861 0.0857
-8.000 -0.3204 0.07518 0.07163 -0.0714 0.9698 0.0905
-7.750 -0.2906 0.07368 0.07016 -0.0691 0.9689 0.0917
-7.500 -0.2708 0.07128 0.06776 -0.0698 0.9615 0.0932
-7.250 -0.2469 0.06735 0.06379 -0.0752 0.9566 0.0960
-7.000 -0.2494 0.05771 0.05378 -0.0892 0.9428 0.1028
-6.750 -0.2992 0.03360 0.02781 -0.0919 0.9267 0.0700
-6.500 -0.2746 0.02987 0.02362 -0.0929 0.9232 0.0701
-6.250 -0.2590 0.02750 0.02098 -0.0915 0.9152 0.0706
-6.000 -0.2319 0.02591 0.01927 -0.0919 0.9103 0.0718
-5.750 -0.1984 0.02498 0.01830 -0.0932 0.9072 0.0738
-5.500 -0.1707 0.02368 0.01675 -0.0933 0.9028 0.0759
-5.250 -0.1513 0.02250 0.01527 -0.0917 0.8949 0.0775
-5.000 -0.1208 0.02136 0.01377 -0.0919 0.8910 0.0793
-4.750 -0.0878 0.02008 0.01250 -0.0930 0.8881 0.0821
-4.500 -0.0679 0.01971 0.01209 -0.0914 0.8794 0.0848
-4.250 -0.0363 0.01900 0.01120 -0.0917 0.8741 0.0888
-4.000 -0.0048 0.01803 0.01018 -0.0920 0.8688 0.0926
-3.750 0.0188 0.01764 0.00979 -0.0909 0.8596 0.0968
-3.500 0.0511 0.01700 0.00900 -0.0912 0.8543 0.1028
-3.250 0.0742 0.01668 0.00876 -0.0901 0.8463 0.1081
-3.000 0.1021 0.01636 0.00833 -0.0897 0.8402 0.1151
-2.750 0.1330 0.01591 0.00794 -0.0900 0.8357 0.1238
-2.500 0.1545 0.01566 0.00769 -0.0886 0.8275 0.1321
-2.250 0.1826 0.01544 0.00746 -0.0883 0.8216 0.1430
-2.000 0.2103 0.01509 0.00716 -0.0880 0.8160 0.1548
-1.750 0.2334 0.01485 0.00695 -0.0869 0.8081 0.1671
-1.500 0.2621 0.01455 0.00664 -0.0867 0.8024 0.1817
-1.250 0.2865 0.01441 0.00652 -0.0858 0.7952 0.1960
-1.000 0.3116 0.01413 0.00632 -0.0850 0.7879 0.2115
-0.750 0.3408 0.01383 0.00605 -0.0849 0.7824 0.2297
-0.500 0.3616 0.01368 0.00602 -0.0834 0.7736 0.2489
-0.250 0.3882 0.01334 0.00582 -0.0829 0.7671 0.2786
0.000 0.4086 0.01294 0.00576 -0.0813 0.7589 0.3471
0.250 0.5865 0.01136 0.00579 -0.1105 0.7526 1.0000
0.500 0.6101 0.01138 0.00569 -0.1094 0.7444 1.0000
0.750 0.6320 0.01139 0.00564 -0.1080 0.7345 1.0000
1.000 0.6546 0.01141 0.00558 -0.1067 0.7249 1.0000
1.250 0.6777 0.01139 0.00545 -0.1054 0.7140 1.0000
1.500 0.6983 0.01141 0.00542 -0.1037 0.7014 1.0000
1.750 0.7202 0.01141 0.00535 -0.1023 0.6889 1.0000
2.000 0.7433 0.01141 0.00524 -0.1010 0.6769 1.0000
2.250 0.7635 0.01145 0.00525 -0.0992 0.6627 1.0000
2.500 0.7840 0.01150 0.00526 -0.0975 0.6480 1.0000
2.750 0.8046 0.01156 0.00525 -0.0958 0.6321 1.0000
3.000 0.8249 0.01164 0.00524 -0.0940 0.6149 1.0000
3.250 0.8449 0.01174 0.00526 -0.0923 0.5973 1.0000
3.500 0.8647 0.01189 0.00531 -0.0905 0.5797 1.0000
3.750 0.8844 0.01207 0.00540 -0.0887 0.5630 1.0000
4.000 0.9040 0.01227 0.00552 -0.0869 0.5468 1.0000
4.250 0.9234 0.01250 0.00566 -0.0851 0.5314 1.0000
4.500 0.9429 0.01276 0.00584 -0.0834 0.5173 1.0000
4.750 0.9627 0.01304 0.00602 -0.0817 0.5048 1.0000
5.000 0.9822 0.01332 0.00623 -0.0800 0.4923 1.0000
5.250 1.0014 0.01360 0.00648 -0.0783 0.4800 1.0000
5.500 1.0213 0.01391 0.00673 -0.0767 0.4696 1.0000
5.750 1.0411 0.01423 0.00700 -0.0751 0.4592 1.0000
6.000 1.0599 0.01452 0.00730 -0.0733 0.4483 1.0000
6.250 1.0790 0.01487 0.00757 -0.0716 0.4375 1.0000
6.500 1.0966 0.01517 0.00786 -0.0696 0.4258 1.0000
6.750 1.1138 0.01547 0.00817 -0.0676 0.4144 1.0000
7.000 1.1313 0.01582 0.00846 -0.0656 0.4034 1.0000
7.250 1.1474 0.01611 0.00877 -0.0634 0.3921 1.0000
7.500 1.1632 0.01642 0.00911 -0.0611 0.3810 1.0000
7.750 1.1784 0.01677 0.00942 -0.0588 0.3697 1.0000
8.000 1.1914 0.01706 0.00974 -0.0560 0.3568 1.0000
8.250 1.2034 0.01738 0.01009 -0.0531 0.3432 1.0000
8.500 1.2129 0.01773 0.01046 -0.0498 0.3288 1.0000
8.750 1.2194 0.01811 0.01082 -0.0460 0.3133 1.0000
9.000 1.2253 0.01856 0.01126 -0.0422 0.2960 1.0000
9.250 1.2309 0.01913 0.01177 -0.0386 0.2770 1.0000
9.500 1.2356 0.01983 0.01240 -0.0351 0.2578 1.0000
9.750 1.2414 0.02062 0.01311 -0.0319 0.2391 1.0000
10.000 1.2472 0.02151 0.01393 -0.0290 0.2228 1.0000
10.250 1.2525 0.02251 0.01485 -0.0262 0.2086 1.0000
10.500 1.2568 0.02365 0.01590 -0.0234 0.1965 1.0000
10.750 1.2633 0.02475 0.01699 -0.0211 0.1850 1.0000
11.000 1.2691 0.02597 0.01819 -0.0188 0.1747 1.0000
11.250 1.2724 0.02742 0.01954 -0.0164 0.1653 1.0000
11.500 1.2789 0.02869 0.02086 -0.0145 0.1555 1.0000
11.750 1.2842 0.03012 0.02228 -0.0126 0.1468 1.0000
12.000 1.2891 0.03159 0.02374 -0.0108 0.1389 1.0000
12.250 1.2958 0.03300 0.02521 -0.0092 0.1312 1.0000
12.500 1.3006 0.03455 0.02673 -0.0077 0.1249 1.0000
12.750 1.3075 0.03602 0.02828 -0.0063 0.1189 1.0000
13.000 1.3128 0.03760 0.02989 -0.0051 0.1134 1.0000
13.250 1.3179 0.03930 0.03158 -0.0038 0.1089 1.0000
13.500 1.3237 0.04095 0.03333 -0.0028 0.1041 1.0000
13.750 1.3279 0.04276 0.03512 -0.0017 0.1003 1.0000
14.000 1.3330 0.04458 0.03700 -0.0007 0.0965 1.0000
14.250 1.3378 0.04645 0.03896 0.0002 0.0929 1.0000
14.500 1.3421 0.04839 0.04089 0.0010 0.0898 1.0000
14.750 1.3482 0.05023 0.04273 0.0019 0.0867 1.0000
15.000 1.3520 0.05234 0.04498 0.0025 0.0838 1.0000
15.250 1.3558 0.05445 0.04714 0.0030 0.0810 1.0000
15.500 1.3641 0.05614 0.04874 0.0038 0.0782 1.0000
15.750 1.3679 0.05837 0.05111 0.0043 0.0760 1.0000
16.000 1.3697 0.06085 0.05374 0.0046 0.0737 1.0000
16.250 1.3730 0.06317 0.05612 0.0048 0.0716 1.0000
16.500 1.3809 0.06498 0.05789 0.0053 0.0694 1.0000
16.750 1.3869 0.06713 0.06011 0.0057 0.0673 1.0000
17.000 1.3829 0.07043 0.06361 0.0054 0.0657 1.0000
17.250 1.3816 0.07349 0.06681 0.0051 0.0640 1.0000
17.500 1.3834 0.07616 0.06955 0.0048 0.0622 1.0000
17.750 1.3954 0.07754 0.07084 0.0053 0.0602 1.0000
18.000 1.3913 0.08111 0.07458 0.0048 0.0590 1.0000
18.250 1.3823 0.08543 0.07913 0.0036 0.0578 1.0000
18.500 1.3743 0.08972 0.08361 0.0023 0.0565 1.0000
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