GOE 571 AIRFOIL (goe571-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 571 AIRFOIL (goe571-il) Reynolds number: 200,000 Max Cl/Cd: 34.03 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe571-il-200000-n5.txt Download as CSV file: xf-goe571-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 571 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 0.5320 0.10959 0.10295 -0.1750 0.5856 0.0397
-12.750 0.5375 0.10750 0.10085 -0.1758 0.5818 0.0405
-12.500 0.5333 0.10526 0.09861 -0.1771 0.5788 0.0414
-12.250 0.5448 0.10314 0.09644 -0.1774 0.5751 0.0416
-12.000 0.5567 0.10127 0.09458 -0.1775 0.5716 0.0421
-11.750 0.5644 0.09938 0.09271 -0.1778 0.5677 0.0426
-11.500 0.5711 0.09749 0.09083 -0.1781 0.5638 0.0432
-11.250 0.5765 0.09556 0.08889 -0.1783 0.5602 0.0438
-11.000 0.5783 0.09350 0.08682 -0.1788 0.5570 0.0450
-10.750 0.5643 0.09098 0.08430 -0.1803 0.5548 0.0456
-10.500 0.5766 0.08907 0.08240 -0.1798 0.5512 0.0458
-10.250 0.5860 0.08730 0.08066 -0.1795 0.5471 0.0461
-10.000 0.5942 0.08560 0.07897 -0.1790 0.5427 0.0467
-9.750 0.5993 0.08390 0.07726 -0.1786 0.5390 0.0477
-9.500 0.6021 0.08215 0.07550 -0.1782 0.5356 0.0481
-9.250 0.5998 0.08011 0.07347 -0.1781 0.5321 0.0494
-9.000 0.5797 0.07702 0.07047 -0.1792 0.5301 0.0503
-8.750 0.5838 0.07523 0.06871 -0.1783 0.5260 0.0504
-8.500 0.5947 0.07403 0.06751 -0.1767 0.5214 0.0510
-8.250 0.5973 0.07252 0.06598 -0.1756 0.5178 0.0516
-8.000 0.5969 0.07099 0.06444 -0.1745 0.5147 0.0535
-7.750 0.5617 0.06731 0.06087 -0.1755 0.5130 0.0551
-7.500 0.5499 0.06482 0.05847 -0.1747 0.5100 0.0554
-7.250 0.5580 0.06389 0.05755 -0.1722 0.5059 0.0558
-7.000 0.5518 0.06229 0.05598 -0.1702 0.5026 0.0563
-6.750 0.5339 0.06040 0.05411 -0.1680 0.4999 0.0565
-6.500 0.5102 0.05876 0.05248 -0.1637 0.4976 0.0568
-6.250 0.4828 0.05748 0.05123 -0.1577 0.4953 0.0569
-5.250 0.3287 0.04318 0.03635 -0.1261 0.4880 0.0370
-5.000 0.3237 0.04200 0.03511 -0.1213 0.4849 0.0368
-4.750 0.3200 0.04080 0.03381 -0.1166 0.4820 0.0365
-4.500 0.3157 0.03937 0.03224 -0.1118 0.4794 0.0362
-4.250 0.3130 0.03801 0.03073 -0.1070 0.4766 0.0359
-4.000 0.3081 0.03629 0.02884 -0.1017 0.4739 0.0356
-3.750 0.3055 0.03479 0.02715 -0.0967 0.4708 0.0350
-3.500 0.3035 0.03316 0.02527 -0.0915 0.4682 0.0347
-3.250 0.3045 0.03181 0.02367 -0.0868 0.4655 0.0346
-3.000 0.3075 0.03054 0.02209 -0.0823 0.4631 0.0343
-2.750 0.3154 0.02967 0.02096 -0.0788 0.4607 0.0344
-2.500 0.3249 0.02914 0.02029 -0.0756 0.4583 0.0348
-2.250 0.3334 0.02866 0.01967 -0.0722 0.4558 0.0355
-2.000 0.3425 0.02807 0.01891 -0.0688 0.4533 0.0355
-1.750 0.3529 0.02754 0.01819 -0.0657 0.4508 0.0355
-1.500 0.3656 0.02706 0.01752 -0.0630 0.4484 0.0355
-1.250 0.3797 0.02665 0.01694 -0.0606 0.4461 0.0355
-1.000 0.3960 0.02629 0.01640 -0.0586 0.4439 0.0355
-0.750 0.4158 0.02593 0.01584 -0.0572 0.4416 0.0356
-0.500 0.4276 0.02577 0.01562 -0.0546 0.4394 0.0358
-0.250 0.4406 0.02569 0.01549 -0.0522 0.4370 0.0358
0.000 0.4545 0.02562 0.01537 -0.0501 0.4346 0.0359
0.250 0.4694 0.02556 0.01523 -0.0481 0.4325 0.0363
0.500 0.4850 0.02554 0.01517 -0.0463 0.4303 0.0364
0.750 0.5030 0.02550 0.01505 -0.0449 0.4285 0.0368
1.000 0.5226 0.02548 0.01495 -0.0438 0.4266 0.0369
1.250 0.5452 0.02538 0.01479 -0.0432 0.4249 0.0374
1.500 0.5655 0.02540 0.01479 -0.0424 0.4232 0.0377
1.750 0.5731 0.02570 0.01516 -0.0397 0.4209 0.0382
2.000 0.5828 0.02601 0.01552 -0.0374 0.4186 0.0386
2.250 0.5958 0.02632 0.01585 -0.0356 0.4167 0.0396
2.500 0.6092 0.02666 0.01618 -0.0340 0.4146 0.0406
2.750 0.6244 0.02698 0.01649 -0.0326 0.4128 0.0413
3.000 0.6418 0.02722 0.01675 -0.0317 0.4111 0.0419
3.250 0.6621 0.02744 0.01694 -0.0312 0.4094 0.0428
3.500 0.6852 0.02763 0.01707 -0.0310 0.4078 0.0435
3.750 0.7136 0.02771 0.01705 -0.0316 0.4061 0.0452
4.000 0.7208 0.02848 0.01788 -0.0296 0.4042 0.0457
4.250 0.7263 0.02938 0.01885 -0.0277 0.4021 0.0469
4.500 0.7348 0.03026 0.01978 -0.0262 0.4000 0.0490
5.000 0.7597 0.03187 0.02152 -0.0244 0.3962 0.0605
5.250 0.7753 0.03259 0.02232 -0.0241 0.3944 0.0842
5.500 1.0832 0.03238 0.02411 -0.0802 0.3917 1.0000
5.750 1.1027 0.03282 0.02444 -0.0798 0.3901 1.0000
6.000 1.1265 0.03310 0.02460 -0.0798 0.3886 1.0000
6.250 1.1260 0.03459 0.02615 -0.0774 0.3869 1.0000
6.500 1.1193 0.03653 0.02819 -0.0746 0.3849 1.0000
6.750 1.1129 0.03859 0.03034 -0.0722 0.3825 1.0000
7.000 1.1106 0.04049 0.03228 -0.0702 0.3800 1.0000
7.250 1.1139 0.04211 0.03391 -0.0688 0.3780 1.0000
7.500 1.1229 0.04331 0.03509 -0.0678 0.3760 1.0000
7.750 1.1357 0.04429 0.03603 -0.0671 0.3744 1.0000
8.000 1.1559 0.04472 0.03638 -0.0670 0.3730 1.0000
8.250 1.1833 0.04464 0.03619 -0.0673 0.3717 1.0000
8.500 1.0690 0.05633 0.04844 -0.0597 0.3642 1.0000
8.750 1.0488 0.06059 0.05278 -0.0578 0.3603 1.0000
9.000 1.0610 0.06177 0.05394 -0.0575 0.3586 1.0000
9.250 1.0815 0.06215 0.05425 -0.0574 0.3574 1.0000
9.500 1.1061 0.06211 0.05414 -0.0576 0.3563 1.0000
9.750 1.1354 0.06164 0.05357 -0.0580 0.3555 1.0000
11.750 0.8270 0.12052 0.11342 -0.0473 0.2940 1.0000
12.000 0.8540 0.11979 0.11263 -0.0475 0.2949 1.0000
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Polar data table (+)
Polar graphs
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