GOE 286 AIRFOIL (goe286-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 286 AIRFOIL (goe286-il) Reynolds number: 50,000 Max Cl/Cd: 27.89 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe286-il-50000.txt Download as CSV file: xf-goe286-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 286 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3927 0.10839 0.10181 -0.0142 1.0000 0.1786
-8.000 -0.3697 0.10241 0.09582 -0.0123 1.0000 0.1851
-7.750 -0.3748 0.10070 0.09422 -0.0140 1.0000 0.1930
-7.500 -0.3652 0.09668 0.09025 -0.0136 1.0000 0.2000
-7.250 -0.3722 0.09522 0.08891 -0.0163 1.0000 0.2094
-7.000 -0.3581 0.09093 0.08465 -0.0142 1.0000 0.2192
-6.500 -0.3621 0.08662 0.08052 -0.0185 1.0000 0.2415
-6.250 -0.3487 0.08253 0.07650 -0.0150 1.0000 0.2524
-6.000 -0.3465 0.07978 0.07384 -0.0145 1.0000 0.2648
-5.750 -0.3457 0.07727 0.07142 -0.0137 1.0000 0.2795
-5.500 -0.3440 0.07480 0.06905 -0.0121 1.0000 0.2960
-5.250 -0.3427 0.07248 0.06682 -0.0100 1.0000 0.3150
-5.000 -0.3477 0.07070 0.06511 -0.0093 1.0000 0.3391
-4.750 -0.3438 0.06814 0.06266 -0.0041 1.0000 0.3635
-4.500 -0.3457 0.06605 0.06069 0.0002 1.0000 0.3936
-4.250 0.0599 0.04160 0.03520 -0.0228 1.0000 1.0000
-4.000 0.0720 0.03975 0.03341 -0.0240 1.0000 1.0000
-3.750 0.0719 0.03872 0.03249 -0.0224 1.0000 0.9952
-3.500 0.0059 0.04132 0.03538 -0.0066 1.0000 0.9511
-3.250 -0.0509 0.04281 0.03716 0.0055 1.0000 0.9111
-3.000 -0.1041 0.04378 0.03841 0.0161 1.0000 0.8806
-2.750 -0.1613 0.04481 0.03971 0.0272 1.0000 0.8623
-2.500 -0.2231 0.04576 0.04091 0.0384 1.0000 0.8459
-2.250 -0.3191 0.04735 0.04281 0.0537 1.0000 0.8117
-2.000 -0.3673 0.04670 0.04232 0.0578 1.0000 0.7793
-1.750 -0.0398 0.03626 0.02746 -0.0509 0.9870 0.1744
-1.500 0.0261 0.03439 0.02481 -0.0579 0.9730 0.1619
-1.250 0.0874 0.03295 0.02290 -0.0641 0.9578 0.1627
-1.000 0.1432 0.03159 0.02125 -0.0692 0.9414 0.1654
-0.750 0.1936 0.03049 0.02001 -0.0730 0.9235 0.1696
-0.500 0.2478 0.02959 0.01884 -0.0769 0.9059 0.1798
-0.250 0.3023 0.02840 0.01773 -0.0810 0.8889 0.2080
0.000 0.3519 0.02622 0.01658 -0.0842 0.8727 0.3441
0.250 0.4016 0.02442 0.01547 -0.0854 0.8554 1.0000
0.500 0.4450 0.02432 0.01503 -0.0869 0.8370 1.0000
0.750 0.4744 0.02458 0.01507 -0.0865 0.8146 1.0000
1.000 0.5067 0.02471 0.01499 -0.0863 0.7951 1.0000
1.250 0.5375 0.02484 0.01494 -0.0857 0.7766 1.0000
1.500 0.5665 0.02501 0.01495 -0.0848 0.7590 1.0000
1.750 0.5906 0.02553 0.01536 -0.0837 0.7397 1.0000
2.000 0.6158 0.02600 0.01571 -0.0828 0.7225 1.0000
2.250 0.6413 0.02646 0.01608 -0.0819 0.7065 1.0000
2.500 0.6667 0.02694 0.01647 -0.0810 0.6914 1.0000
2.750 0.6920 0.02742 0.01686 -0.0800 0.6770 1.0000
3.000 0.7174 0.02787 0.01723 -0.0789 0.6630 1.0000
3.250 0.7436 0.02823 0.01751 -0.0778 0.6499 1.0000
3.500 0.7683 0.02879 0.01801 -0.0768 0.6363 1.0000
3.750 0.7913 0.02958 0.01878 -0.0760 0.6223 1.0000
4.000 0.8138 0.03045 0.01969 -0.0752 0.6089 1.0000
4.250 0.8364 0.03140 0.02066 -0.0745 0.5969 1.0000
4.500 0.8630 0.03192 0.02114 -0.0737 0.5875 1.0000
4.750 0.8833 0.03320 0.02252 -0.0733 0.5759 1.0000
5.000 0.9030 0.03456 0.02400 -0.0728 0.5649 1.0000
5.250 0.9310 0.03493 0.02434 -0.0719 0.5566 1.0000
5.500 0.9471 0.03667 0.02626 -0.0715 0.5452 1.0000
5.750 0.9656 0.03813 0.02784 -0.0709 0.5350 1.0000
6.000 0.9957 0.03813 0.02787 -0.0698 0.5262 1.0000
6.250 1.0104 0.03978 0.02969 -0.0690 0.5137 1.0000
6.500 1.0280 0.04102 0.03107 -0.0679 0.5014 1.0000
6.750 1.0491 0.04197 0.03214 -0.0669 0.4906 1.0000
7.000 1.0819 0.04152 0.03173 -0.0656 0.4806 1.0000
7.250 1.0988 0.04269 0.03307 -0.0643 0.4669 1.0000
7.500 1.1208 0.04311 0.03361 -0.0628 0.4522 1.0000
7.750 1.1480 0.04277 0.03335 -0.0611 0.4363 1.0000
8.000 1.1770 0.04220 0.03278 -0.0594 0.4196 1.0000
8.250 1.1962 0.04289 0.03359 -0.0577 0.4021 1.0000
8.500 1.2129 0.04405 0.03490 -0.0561 0.3851 1.0000
8.750 1.2300 0.04527 0.03629 -0.0545 0.3687 1.0000
9.000 1.2476 0.04646 0.03760 -0.0530 0.3534 1.0000
9.250 1.2676 0.04746 0.03869 -0.0516 0.3394 1.0000
9.500 1.2940 0.04789 0.03916 -0.0505 0.3264 1.0000
9.750 1.2846 0.05194 0.04362 -0.0484 0.3157 1.0000
10.000 1.2860 0.05476 0.04669 -0.0466 0.3055 1.0000
10.250 1.3085 0.05525 0.04729 -0.0451 0.2934 1.0000
10.500 1.3307 0.05542 0.04757 -0.0435 0.2796 1.0000
10.750 1.2820 0.06313 0.05561 -0.0410 0.2762 1.0000
11.000 1.3578 0.05697 0.04938 -0.0393 0.2504 1.0000
11.250 1.3111 0.06396 0.05669 -0.0365 0.2481 1.0000
11.500 1.2476 0.07382 0.06662 -0.0362 0.2502 1.0000
11.750 1.3078 0.06846 0.06142 -0.0321 0.2253 1.0000
12.000 1.3892 0.05712 0.04939 -0.0282 0.1789 1.0000
12.250 1.3075 0.07117 0.06421 -0.0283 0.1983 1.0000
12.500 1.2770 0.07822 0.07137 -0.0293 0.1963 1.0000
13.000 1.3745 0.06785 0.05995 -0.0203 0.1291 1.0000
13.250 1.3348 0.07460 0.06721 -0.0210 0.1323 1.0000
13.500 1.2924 0.08340 0.07639 -0.0241 0.1370 1.0000
13.750 1.2553 0.09286 0.08605 -0.0281 0.1396 1.0000
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Polar data table (+)
Polar graphs
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