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GOE 561 AIRFOIL (goe561-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
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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