GOE 506 AIRFOIL (goe506-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 506 AIRFOIL (goe506-il) Reynolds number: 200,000 Max Cl/Cd: 58.04 at α=1.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe506-il-200000.txt Download as CSV file: xf-goe506-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 506 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2244 0.10902 0.10566 -0.0793 0.9710 0.0749
-10.750 -0.2199 0.10681 0.10347 -0.0789 0.9653 0.0775
-10.500 -0.2676 0.09469 0.09144 -0.0950 0.9596 0.0841
-10.250 -0.2212 0.09623 0.09292 -0.0884 0.9594 0.0865
-10.000 -0.1979 0.09437 0.09105 -0.0897 0.9581 0.0906
-9.750 -0.0839 0.08008 0.07687 -0.0994 0.9428 0.1046
-9.500 -0.2182 0.08465 0.08141 -0.0962 0.9467 0.0999
-9.250 -0.1957 0.08268 0.07941 -0.0976 0.9449 0.1040
-8.750 -0.4837 0.04800 0.04298 -0.0977 0.9067 0.0498
-8.500 -0.4854 0.04454 0.03936 -0.0947 0.9018 0.0480
-8.250 -0.4776 0.04184 0.03629 -0.0929 0.8989 0.0477
-8.000 -0.4628 0.03909 0.03315 -0.0918 0.8970 0.0470
-7.750 -0.4788 0.03830 0.03217 -0.0847 0.8905 0.0465
-7.500 -0.4729 0.03662 0.03017 -0.0813 0.8866 0.0459
-7.250 -0.4544 0.03482 0.02803 -0.0799 0.8840 0.0456
-7.000 -0.4288 0.03323 0.02619 -0.0797 0.8822 0.0461
-6.750 -0.3955 0.03193 0.02467 -0.0808 0.8807 0.0477
-6.500 -0.4037 0.03185 0.02449 -0.0746 0.8733 0.0485
-6.250 -0.3712 0.03056 0.02299 -0.0751 0.8687 0.0496
-6.000 -0.3237 0.02912 0.02134 -0.0781 0.8660 0.0506
-5.750 -0.2817 0.02710 0.01940 -0.0807 0.8645 0.0536
-5.500 -0.2895 0.02715 0.01943 -0.0744 0.8552 0.0544
-5.250 -0.2546 0.02618 0.01843 -0.0754 0.8521 0.0567
-5.000 -0.2143 0.02515 0.01735 -0.0773 0.8500 0.0591
-4.750 -0.2018 0.02486 0.01702 -0.0745 0.8438 0.0609
-4.500 -0.1805 0.02404 0.01623 -0.0732 0.8381 0.0642
-4.250 -0.1388 0.02302 0.01515 -0.0752 0.8354 0.0688
-4.000 -0.0925 0.02183 0.01390 -0.0781 0.8339 0.0771
-3.750 -0.0935 0.02201 0.01404 -0.0727 0.8244 0.0831
-3.500 -0.0633 0.02072 0.01339 -0.0731 0.8214 0.2127
-3.250 -0.0199 0.02018 0.01290 -0.0755 0.8198 0.2630
-3.000 0.0255 0.01961 0.01231 -0.0783 0.8185 0.2909
-2.750 0.0223 0.02009 0.01280 -0.0726 0.8087 0.2987
-2.500 0.0635 0.01947 0.01214 -0.0747 0.8065 0.3137
-2.250 0.1090 0.01873 0.01141 -0.0775 0.8049 0.3304
-2.000 0.1573 0.01799 0.01067 -0.0810 0.8036 0.3467
-1.750 0.1629 0.01807 0.01078 -0.0766 0.7951 0.3560
-1.500 0.2009 0.01745 0.01019 -0.0781 0.7916 0.3769
-1.250 0.2479 0.01659 0.00946 -0.0814 0.7894 0.4048
-1.000 0.2995 0.01563 0.00865 -0.0856 0.7873 0.4445
-0.750 0.2981 0.01549 0.00867 -0.0795 0.7771 0.4729
-0.500 0.3418 0.01434 0.00793 -0.0820 0.7731 0.5677
-0.250 0.3472 0.01377 0.00784 -0.0769 0.7637 0.6827
0.000 0.5037 0.01258 0.00711 -0.1015 0.7554 0.9102
0.250 0.5673 0.01250 0.00692 -0.1081 0.7409 0.9430
0.500 0.6162 0.01250 0.00680 -0.1119 0.7229 0.9645
0.750 0.6637 0.01252 0.00668 -0.1157 0.6975 0.9814
1.000 0.7151 0.01251 0.00646 -0.1204 0.6526 0.9939
1.250 0.7377 0.01271 0.00611 -0.1194 0.5671 1.0000
1.500 0.7238 0.01318 0.00617 -0.1113 0.5249 1.0000
1.750 0.7169 0.01360 0.00632 -0.1046 0.4995 1.0000
2.000 0.7161 0.01395 0.00648 -0.0991 0.4802 1.0000
2.250 0.7214 0.01428 0.00664 -0.0949 0.4649 1.0000
2.500 0.7305 0.01460 0.00682 -0.0914 0.4526 1.0000
2.750 0.7421 0.01489 0.00699 -0.0884 0.4420 1.0000
3.000 0.7564 0.01517 0.00717 -0.0859 0.4332 1.0000
3.250 0.7716 0.01546 0.00736 -0.0836 0.4257 1.0000
3.500 0.7889 0.01574 0.00755 -0.0818 0.4191 1.0000
3.750 0.8061 0.01600 0.00776 -0.0799 0.4128 1.0000
4.000 0.8256 0.01632 0.00796 -0.0786 0.4075 1.0000
4.250 0.8443 0.01657 0.00819 -0.0770 0.4022 1.0000
4.500 0.8638 0.01683 0.00843 -0.0757 0.3976 1.0000
4.750 0.8854 0.01713 0.00866 -0.0747 0.3935 1.0000
5.000 0.9092 0.01746 0.00891 -0.0742 0.3898 1.0000
5.250 0.9283 0.01771 0.00919 -0.0728 0.3857 1.0000
5.500 0.9484 0.01799 0.00947 -0.0716 0.3817 1.0000
5.750 0.9708 0.01829 0.00973 -0.0708 0.3782 1.0000
6.000 0.9991 0.01866 0.01000 -0.0712 0.3750 1.0000
6.250 1.0180 0.01894 0.01035 -0.0698 0.3718 1.0000
6.500 1.0385 0.01924 0.01069 -0.0688 0.3686 1.0000
6.750 1.0600 0.01955 0.01102 -0.0679 0.3654 1.0000
7.000 1.0826 0.01988 0.01134 -0.0672 0.3621 1.0000
7.250 1.1118 0.02028 0.01167 -0.0679 0.3586 1.0000
7.500 1.1260 0.02059 0.01208 -0.0657 0.3551 1.0000
7.750 1.1428 0.02091 0.01248 -0.0640 0.3511 1.0000
8.000 1.1630 0.02126 0.01284 -0.0630 0.3475 1.0000
8.250 1.1884 0.02164 0.01320 -0.0630 0.3442 1.0000
8.500 1.2074 0.02204 0.01366 -0.0618 0.3405 1.0000
8.750 1.2224 0.02242 0.01415 -0.0599 0.3370 1.0000
9.000 1.2395 0.02280 0.01459 -0.0585 0.3330 1.0000
9.250 1.2595 0.02319 0.01495 -0.0575 0.3286 1.0000
9.500 1.2723 0.02365 0.01548 -0.0554 0.3235 1.0000
9.750 1.2797 0.02408 0.01603 -0.0525 0.3176 1.0000
10.000 1.2951 0.02451 0.01638 -0.0510 0.3113 1.0000
10.250 1.2987 0.02508 0.01710 -0.0476 0.3052 1.0000
10.500 1.3065 0.02561 0.01771 -0.0451 0.2988 1.0000
10.750 1.3178 0.02619 0.01829 -0.0431 0.2928 1.0000
11.000 1.3219 0.02688 0.01914 -0.0402 0.2857 1.0000
11.250 1.3315 0.02754 0.01978 -0.0382 0.2794 1.0000
11.500 1.3364 0.02837 0.02079 -0.0357 0.2716 1.0000
11.750 1.3413 0.02924 0.02164 -0.0334 0.2636 1.0000
12.000 1.3477 0.03017 0.02274 -0.0313 0.2535 1.0000
12.250 1.3551 0.03115 0.02380 -0.0295 0.2446 1.0000
12.500 1.3604 0.03229 0.02498 -0.0276 0.2336 1.0000
12.750 1.3651 0.03359 0.02631 -0.0258 0.2197 1.0000
13.000 1.3658 0.03525 0.02792 -0.0239 0.2031 1.0000
13.250 1.3625 0.03731 0.02990 -0.0218 0.1892 1.0000
13.500 1.3578 0.03963 0.03216 -0.0198 0.1784 1.0000
13.750 1.3530 0.04210 0.03461 -0.0180 0.1695 1.0000
14.000 1.3492 0.04460 0.03714 -0.0164 0.1600 1.0000
14.250 1.3420 0.04751 0.04006 -0.0149 0.1512 1.0000
14.500 1.3392 0.05019 0.04281 -0.0139 0.1414 1.0000
14.750 1.3362 0.05304 0.04572 -0.0131 0.1264 1.0000
15.000 1.3185 0.05758 0.05009 -0.0123 0.0819 1.0000
15.250 1.2971 0.06276 0.05520 -0.0119 0.0684 1.0000
15.750 1.2505 0.07448 0.06693 -0.0124 0.0401 1.0000
16.000 1.2370 0.07945 0.07197 -0.0131 0.0372 1.0000
16.250 1.2222 0.08475 0.07738 -0.0140 0.0350 1.0000
16.500 1.2092 0.08987 0.08262 -0.0150 0.0338 1.0000
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Polar data table (+)
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