GOE 561 AIRFOIL (goe561-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 561 AIRFOIL (goe561-il) Reynolds number: 200,000 Max Cl/Cd: 20.88 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe561-il-200000-n5.txt Download as CSV file: xf-goe561-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 561 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
------ -------- --------- --------- -------- -------- --------
-12.750 0.5590 0.10783 0.10091 -0.1740 0.5526 0.0374
-12.500 0.5672 0.10581 0.09889 -0.1750 0.5499 0.0381
-12.250 0.5747 0.10382 0.09689 -0.1758 0.5471 0.0386
-12.000 0.5800 0.10180 0.09487 -0.1768 0.5449 0.0391
-11.750 0.5783 0.09984 0.09291 -0.1781 0.5429 0.0395
-11.500 0.5833 0.09786 0.09090 -0.1788 0.5404 0.0396
-11.250 0.5955 0.09579 0.08880 -0.1790 0.5381 0.0398
-10.750 0.6154 0.09207 0.08505 -0.1795 0.5332 0.0406
-10.500 0.6221 0.09024 0.08324 -0.1798 0.5313 0.0410
-10.250 0.6280 0.08845 0.08148 -0.1800 0.5293 0.0414
-10.000 0.6328 0.08660 0.07965 -0.1802 0.5272 0.0420
-9.750 0.6366 0.08481 0.07787 -0.1802 0.5252 0.0424
-9.500 0.6377 0.08290 0.07598 -0.1804 0.5233 0.0431
-9.250 0.6300 0.08076 0.07387 -0.1809 0.5219 0.0436
-9.000 0.6305 0.07892 0.07203 -0.1808 0.5198 0.0437
-8.750 0.6248 0.07680 0.06992 -0.1811 0.5181 0.0438
-8.500 0.6290 0.07485 0.06797 -0.1807 0.5163 0.0439
-8.250 0.6348 0.07305 0.06616 -0.1805 0.5147 0.0440
-8.000 0.6410 0.07149 0.06462 -0.1796 0.5131 0.0443
-7.750 0.6399 0.06984 0.06303 -0.1785 0.5116 0.0445
-7.500 0.6389 0.06826 0.06151 -0.1772 0.5098 0.0451
-7.250 0.6313 0.06651 0.05983 -0.1757 0.5078 0.0452
-7.000 0.6229 0.06476 0.05814 -0.1744 0.5062 0.0458
-6.750 0.6065 0.06282 0.05626 -0.1728 0.5045 0.0460
-6.500 0.5858 0.06113 0.05462 -0.1695 0.5028 0.0462
-6.250 0.5617 0.05972 0.05324 -0.1646 0.5015 0.0462
-6.000 0.5335 0.05869 0.05224 -0.1579 0.4999 0.0466
-5.750 0.5114 0.05743 0.05098 -0.1521 0.4984 0.0465
-5.500 0.4909 0.05604 0.04956 -0.1465 0.4970 0.0471
-5.250 0.4540 0.05407 0.04742 -0.1384 0.4958 0.0481
-5.000 0.4321 0.05229 0.04543 -0.1318 0.4945 0.0483
-4.750 0.4301 0.05078 0.04386 -0.1280 0.4926 0.0484
-4.500 0.4306 0.04983 0.04307 -0.1243 0.4908 0.0487
-4.250 0.4231 0.04872 0.04196 -0.1191 0.4890 0.0489
-4.000 0.4164 0.04765 0.04090 -0.1140 0.4869 0.0492
-3.750 0.4108 0.04652 0.03974 -0.1090 0.4849 0.0496
-3.500 0.4058 0.04534 0.03851 -0.1040 0.4830 0.0498
-3.250 0.4020 0.04416 0.03725 -0.0991 0.4810 0.0501
-2.750 0.3804 0.03905 0.03146 -0.0846 0.4780 0.0395
-2.500 0.3863 0.03813 0.03047 -0.0812 0.4762 0.0392
-2.250 0.3948 0.03720 0.02943 -0.0781 0.4744 0.0388
-2.000 0.4028 0.03613 0.02818 -0.0747 0.4726 0.0383
-1.750 0.3968 0.03545 0.02744 -0.0687 0.4706 0.0379
-1.500 0.3936 0.03480 0.02670 -0.0632 0.4685 0.0376
-1.250 0.3927 0.03411 0.02589 -0.0580 0.4663 0.0374
-1.000 0.3933 0.03348 0.02512 -0.0531 0.4640 0.0375
-0.750 0.3968 0.03280 0.02427 -0.0487 0.4619 0.0371
-0.500 0.4024 0.03220 0.02351 -0.0447 0.4597 0.0372
-0.250 0.4117 0.03164 0.02279 -0.0414 0.4578 0.0373
0.000 0.4260 0.03103 0.02196 -0.0388 0.4557 0.0379
0.250 0.4463 0.03028 0.02090 -0.0371 0.4538 0.0388
0.500 0.4433 0.03033 0.02094 -0.0322 0.4513 0.0387
0.750 0.4439 0.03032 0.02089 -0.0279 0.4485 0.0387
1.000 0.4505 0.03023 0.02070 -0.0247 0.4459 0.0388
1.250 0.4617 0.03004 0.02038 -0.0222 0.4432 0.0389
1.500 0.4779 0.02981 0.02000 -0.0206 0.4409 0.0391
1.750 0.5011 0.02947 0.01946 -0.0201 0.4388 0.0394
2.000 0.5314 0.02904 0.01889 -0.0210 0.4365 0.0398
2.250 0.5412 0.02935 0.01922 -0.0190 0.4338 0.0400
2.500 0.5405 0.03007 0.02002 -0.0158 0.4302 0.0404
2.750 0.5511 0.03050 0.02044 -0.0143 0.4267 0.0405
3.000 0.5670 0.03082 0.02075 -0.0135 0.4239 0.0414
3.250 0.5932 0.03083 0.02069 -0.0142 0.4215 0.0425
3.500 0.6254 0.03065 0.02039 -0.0156 0.4193 0.0442
3.750 0.6244 0.03186 0.02171 -0.0133 0.4153 0.0448
4.000 0.6271 0.03306 0.02299 -0.0116 0.4114 0.0450
4.250 0.6415 0.03381 0.02376 -0.0114 0.4077 0.0458
4.500 0.6686 0.03400 0.02391 -0.0125 0.4051 0.0469
4.750 0.7002 0.03394 0.02376 -0.0141 0.4029 0.0481
5.000 0.6925 0.03607 0.02602 -0.0119 0.3983 0.0484
5.250 0.6939 0.03785 0.02790 -0.0109 0.3938 0.0495
5.500 0.7140 0.03855 0.02860 -0.0116 0.3905 0.0508
5.750 0.7436 0.03871 0.02871 -0.0131 0.3883 0.0541
6.000 0.7509 0.04035 0.03039 -0.0129 0.3840 0.0555
6.250 0.7390 0.04336 0.03350 -0.0112 0.3785 0.0563
6.500 0.7555 0.04440 0.03450 -0.0116 0.3753 0.0585
6.750 0.7833 0.04459 0.03464 -0.0128 0.3732 0.0611
7.000 0.8165 0.04438 0.03433 -0.0143 0.3714 0.0681
7.250 0.7732 0.05006 0.04022 -0.0108 0.3642 0.0672
7.500 0.7830 0.05171 0.04189 -0.0108 0.3607 0.0756
7.750 1.0878 0.05247 0.04453 -0.0646 0.3595 1.0000
8.000 1.1062 0.05298 0.04493 -0.0643 0.3573 1.0000
8.250 1.1111 0.05477 0.04670 -0.0634 0.3543 1.0000
8.500 1.0802 0.06012 0.05222 -0.0610 0.3486 1.0000
8.750 1.0840 0.06213 0.05421 -0.0602 0.3455 1.0000
9.000 1.0995 0.06297 0.05498 -0.0599 0.3435 1.0000
9.250 1.1214 0.06317 0.05508 -0.0600 0.3419 1.0000
9.500 1.1105 0.06676 0.05874 -0.0587 0.3382 1.0000
9.750 1.0742 0.07319 0.06534 -0.0566 0.3323 1.0000
10.000 1.0805 0.07509 0.06722 -0.0562 0.3297 1.0000
10.250 1.1008 0.07543 0.06748 -0.0562 0.3283 1.0000
10.500 1.1246 0.07537 0.06733 -0.0564 0.3270 1.0000
10.750 1.1520 0.07490 0.06676 -0.0567 0.3258 1.0000
11.250 0.9469 0.10481 0.09743 -0.0502 0.3031 1.0000
11.500 0.9473 0.10767 0.10029 -0.0499 0.3003 1.0000
11.750 0.9667 0.10805 0.10062 -0.0501 0.2992 1.0000
12.000 0.9842 0.10868 0.10121 -0.0502 0.2984 1.0000
12.250 1.0040 0.10899 0.10147 -0.0503 0.2977 1.0000
12.500 1.0296 0.10853 0.10096 -0.0506 0.2971 1.0000
12.750 1.0536 0.10829 0.10066 -0.0509 0.2965 1.0000
13.000 1.0773 0.10808 0.10039 -0.0512 0.2960 1.0000
14.000 0.9112 0.14321 0.13604 -0.0497 0.2675 1.0000
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