GOE 526 AIRFOIL (goe526-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 526 AIRFOIL (goe526-il) Reynolds number: 100,000 Max Cl/Cd: 52.85 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe526-il-100000-n5.txt Download as CSV file: xf-goe526-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3388 0.09678 0.09150 -0.0432 1.0000 0.0581
-9.250 -0.3511 0.09441 0.08922 -0.0419 1.0000 0.0582
-9.000 -0.3586 0.09149 0.08637 -0.0422 0.9982 0.0585
-8.750 -0.3500 0.08615 0.08102 -0.0483 0.9902 0.0587
-8.500 -0.3435 0.08043 0.07529 -0.0552 0.9815 0.0587
-8.250 -0.3425 0.07399 0.06883 -0.0632 0.9701 0.0582
-8.000 -0.3415 0.06642 0.06116 -0.0716 0.9574 0.0580
-7.750 -0.3440 0.05815 0.05268 -0.0788 0.9449 0.0580
-7.500 -0.3484 0.04935 0.04346 -0.0838 0.9333 0.0590
-7.250 -0.3493 0.04063 0.03395 -0.0869 0.9247 0.0605
-7.000 -0.3476 0.03591 0.02853 -0.0856 0.9136 0.0614
-6.750 -0.3259 0.03303 0.02520 -0.0861 0.9087 0.0624
-6.500 -0.3057 0.03185 0.02389 -0.0854 0.9012 0.0634
-6.250 -0.2807 0.03077 0.02267 -0.0854 0.8953 0.0651
-6.000 -0.2525 0.02920 0.02080 -0.0861 0.8913 0.0673
-5.750 -0.2341 0.02768 0.01889 -0.0847 0.8838 0.0693
-5.500 -0.2087 0.02631 0.01722 -0.0845 0.8783 0.0710
-5.250 -0.1777 0.02545 0.01631 -0.0853 0.8746 0.0728
-5.000 -0.1546 0.02481 0.01558 -0.0845 0.8681 0.0753
-4.750 -0.1289 0.02399 0.01450 -0.0841 0.8624 0.0788
-4.500 -0.0984 0.02321 0.01367 -0.0846 0.8583 0.0818
-4.250 -0.0706 0.02267 0.01308 -0.0845 0.8535 0.0850
-4.000 -0.0474 0.02218 0.01245 -0.0836 0.8467 0.0891
-3.500 0.0154 0.02111 0.01131 -0.0846 0.8384 0.0995
-3.250 0.0358 0.02078 0.01095 -0.0830 0.8287 0.1048
-3.000 0.0690 0.02026 0.01040 -0.0836 0.8224 0.1122
-2.750 0.0925 0.01991 0.01003 -0.0824 0.8125 0.1194
-2.500 0.1232 0.01949 0.00955 -0.0826 0.8057 0.1291
-2.250 0.1484 0.01921 0.00932 -0.0819 0.7985 0.1380
-2.000 0.1740 0.01894 0.00902 -0.0812 0.7912 0.1489
-1.750 0.2052 0.01860 0.00865 -0.0815 0.7860 0.1618
-1.500 0.2263 0.01842 0.00855 -0.0801 0.7774 0.1726
-1.250 0.2542 0.01814 0.00828 -0.0798 0.7709 0.1866
-1.000 0.2807 0.01792 0.00809 -0.0793 0.7640 0.2017
-0.750 0.3050 0.01775 0.00796 -0.0784 0.7557 0.2186
-0.500 0.3359 0.01741 0.00769 -0.0786 0.7499 0.2402
-0.250 0.3574 0.01728 0.00770 -0.0773 0.7404 0.2662
0.000 0.3872 0.01689 0.00750 -0.0775 0.7335 0.3182
0.250 0.4069 0.01623 0.00753 -0.0759 0.7246 0.4865
0.750 0.5800 0.01524 0.00743 -0.0980 0.7075 1.0000
1.000 0.6034 0.01527 0.00734 -0.0968 0.6983 1.0000
1.250 0.6234 0.01539 0.00740 -0.0951 0.6873 1.0000
1.500 0.6472 0.01541 0.00731 -0.0940 0.6776 1.0000
1.750 0.6670 0.01553 0.00738 -0.0922 0.6655 1.0000
2.000 0.6878 0.01563 0.00742 -0.0907 0.6538 1.0000
2.250 0.7108 0.01569 0.00739 -0.0894 0.6428 1.0000
2.500 0.7309 0.01582 0.00747 -0.0877 0.6296 1.0000
2.750 0.7509 0.01594 0.00754 -0.0860 0.6154 1.0000
3.000 0.7713 0.01605 0.00759 -0.0843 0.6005 1.0000
3.250 0.7916 0.01618 0.00764 -0.0826 0.5851 1.0000
3.500 0.8120 0.01633 0.00771 -0.0809 0.5700 1.0000
3.750 0.8321 0.01649 0.00779 -0.0792 0.5546 1.0000
4.000 0.8520 0.01669 0.00789 -0.0775 0.5390 1.0000
4.250 0.8720 0.01690 0.00802 -0.0758 0.5244 1.0000
4.500 0.8918 0.01716 0.00821 -0.0741 0.5109 1.0000
4.750 0.9114 0.01743 0.00844 -0.0724 0.4984 1.0000
5.000 0.9310 0.01772 0.00866 -0.0708 0.4860 1.0000
5.250 0.9506 0.01803 0.00887 -0.0691 0.4738 1.0000
5.500 0.9692 0.01836 0.00916 -0.0673 0.4614 1.0000
5.750 0.9879 0.01871 0.00948 -0.0656 0.4499 1.0000
6.000 1.0078 0.01907 0.00977 -0.0640 0.4401 1.0000
6.250 1.0265 0.01943 0.01017 -0.0624 0.4305 1.0000
6.500 1.0463 0.01981 0.01051 -0.0609 0.4217 1.0000
6.750 1.0642 0.02020 0.01094 -0.0591 0.4116 1.0000
7.000 1.0823 0.02061 0.01134 -0.0574 0.4019 1.0000
7.250 1.0989 0.02102 0.01174 -0.0554 0.3908 1.0000
7.500 1.1136 0.02144 0.01220 -0.0531 0.3786 1.0000
7.750 1.1272 0.02187 0.01264 -0.0507 0.3658 1.0000
8.000 1.1391 0.02233 0.01307 -0.0480 0.3522 1.0000
8.250 1.1486 0.02279 0.01355 -0.0449 0.3383 1.0000
8.500 1.1575 0.02328 0.01408 -0.0418 0.3246 1.0000
8.750 1.1663 0.02383 0.01466 -0.0388 0.3108 1.0000
9.000 1.1747 0.02443 0.01527 -0.0358 0.2962 1.0000
9.250 1.1823 0.02512 0.01596 -0.0330 0.2804 1.0000
9.500 1.1891 0.02590 0.01672 -0.0302 0.2637 1.0000
9.750 1.1954 0.02679 0.01758 -0.0275 0.2469 1.0000
10.000 1.2009 0.02779 0.01855 -0.0249 0.2311 1.0000
10.250 1.2058 0.02890 0.01961 -0.0224 0.2166 1.0000
10.500 1.2103 0.03013 0.02079 -0.0200 0.2040 1.0000
10.750 1.2141 0.03147 0.02208 -0.0178 0.1936 1.0000
11.000 1.2181 0.03289 0.02348 -0.0157 0.1840 1.0000
11.250 1.2226 0.03435 0.02496 -0.0139 0.1753 1.0000
11.500 1.2253 0.03599 0.02657 -0.0120 0.1676 1.0000
11.750 1.2307 0.03752 0.02816 -0.0105 0.1601 1.0000
12.000 1.2333 0.03929 0.02994 -0.0089 0.1529 1.0000
12.250 1.2379 0.04098 0.03170 -0.0076 0.1462 1.0000
12.500 1.2415 0.04279 0.03359 -0.0064 0.1394 1.0000
12.750 1.2444 0.04471 0.03552 -0.0052 0.1338 1.0000
13.000 1.2486 0.04659 0.03754 -0.0042 0.1273 1.0000
13.250 1.2501 0.04871 0.03967 -0.0033 0.1225 1.0000
13.500 1.2539 0.05075 0.04183 -0.0025 0.1172 1.0000
13.750 1.2562 0.05296 0.04411 -0.0019 0.1125 1.0000
14.000 1.2569 0.05533 0.04647 -0.0013 0.1090 1.0000
14.250 1.2605 0.05759 0.04889 -0.0008 0.1046 1.0000
14.500 1.2620 0.06005 0.05144 -0.0005 0.1010 1.0000
14.750 1.2625 0.06265 0.05404 -0.0003 0.0980 1.0000
15.000 1.2652 0.06513 0.05662 -0.0001 0.0949 1.0000
15.250 1.2668 0.06780 0.05941 -0.0001 0.0919 1.0000
15.500 1.2678 0.07056 0.06224 -0.0002 0.0893 1.0000
15.750 1.2699 0.07315 0.06482 -0.0002 0.0870 1.0000
16.000 1.2712 0.07601 0.06781 -0.0004 0.0846 1.0000
16.250 1.2715 0.07909 0.07104 -0.0007 0.0822 1.0000
16.500 1.2716 0.08219 0.07424 -0.0012 0.0800 1.0000
16.750 1.2727 0.08514 0.07723 -0.0017 0.0780 1.0000
17.000 1.2766 0.08762 0.07971 -0.0019 0.0760 1.0000
17.250 1.2708 0.09189 0.08422 -0.0031 0.0743 1.0000
17.500 1.2655 0.09610 0.08862 -0.0045 0.0725 1.0000
17.750 1.2610 0.10021 0.09287 -0.0059 0.0707 1.0000
18.000 1.2590 0.10389 0.09664 -0.0071 0.0691 1.0000
18.250 1.2638 0.10631 0.09903 -0.0077 0.0673 1.0000
18.500 1.2541 0.11151 0.10441 -0.0099 0.0661 1.0000
18.750 1.2365 0.11835 0.11152 -0.0133 0.0649 1.0000
19.000 1.2164 0.12585 0.11926 -0.0172 0.0637 1.0000
19.250 1.1929 0.13431 0.12794 -0.0220 0.0627 1.0000
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Polar data table (+)
Polar graphs
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