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GOE 561 AIRFOIL (goe561-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 561 AIRFOIL (goe561-il)
Reynolds number: 500,000
Max Cl/Cd: 32.97 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe561-il-500000-n5.txt
Download as CSV file: xf-goe561-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000   0.5528   0.09900   0.09337  -0.1702   0.4997   0.0256
 -11.750   0.5598   0.09707   0.09144  -0.1706   0.4981   0.0260
 -11.500   0.5666   0.09518   0.08954  -0.1711   0.4962   0.0263
 -11.250   0.5728   0.09326   0.08761  -0.1714   0.4944   0.0265
 -11.000   0.5759   0.09101   0.08536  -0.1721   0.4930   0.0276
 -10.750   0.5810   0.08897   0.08335  -0.1725   0.4922   0.0277
 -10.500   0.5817   0.08664   0.08104  -0.1730   0.4909   0.0279
 -10.250   0.5827   0.08443   0.07885  -0.1735   0.4899   0.0279
 -10.000   0.5836   0.08213   0.07659  -0.1739   0.4887   0.0280
  -9.750   0.5861   0.08004   0.07452  -0.1740   0.4876   0.0280
  -9.500   0.5800   0.07720   0.07172  -0.1747   0.4866   0.0281
  -9.250   0.5846   0.07524   0.06977  -0.1742   0.4854   0.0282
  -9.000   0.5809   0.07282   0.06738  -0.1745   0.4842   0.0281
  -8.750   0.5793   0.07057   0.06516  -0.1742   0.4827   0.0281
  -8.250   0.5732   0.06627   0.06090  -0.1731   0.4795   0.0281
  -8.000   0.5656   0.06395   0.05860  -0.1724   0.4779   0.0281
  -7.750   0.5584   0.06189   0.05657  -0.1716   0.4766   0.0280
  -7.500   0.5684   0.06175   0.05643  -0.1689   0.4743   0.0284
  -7.250   0.5292   0.05777   0.05250  -0.1687   0.4737   0.0280
  -7.000   0.4981   0.05560   0.05034  -0.1640   0.4727   0.0280
  -6.750   0.4766   0.05458   0.04937  -0.1582   0.4716   0.0280
  -6.500   0.4588   0.05392   0.04876  -0.1522   0.4706   0.0279
  -6.250   0.4612   0.05379   0.04868  -0.1487   0.4692   0.0274
  -6.000   0.4377   0.05214   0.04705  -0.1425   0.4677   0.0274
  -5.750   0.4223   0.05076   0.04568  -0.1372   0.4663   0.0267
  -5.500   0.4043   0.04893   0.04382  -0.1316   0.4654   0.0264
  -5.250   0.3890   0.04724   0.04209  -0.1260   0.4641   0.0264
  -5.000   0.3722   0.04517   0.03995  -0.1199   0.4627   0.0260
  -4.750   0.3445   0.04181   0.03643  -0.1118   0.4616   0.0252
  -4.500   0.3500   0.04153   0.03615  -0.1087   0.4600   0.0257
  -4.250   0.3344   0.03905   0.03351  -0.1019   0.4585   0.0254
  -4.000   0.3231   0.03695   0.03126  -0.0954   0.4572   0.0252
  -3.750   0.3242   0.03608   0.03031  -0.0912   0.4555   0.0254
  -3.500   0.3212   0.03470   0.02879  -0.0860   0.4537   0.0255
  -3.250   0.3250   0.03381   0.02784  -0.0820   0.4528   0.0257
  -3.000   0.3255   0.03257   0.02651  -0.0772   0.4514   0.0259
  -2.750   0.3222   0.03092   0.02469  -0.0714   0.4502   0.0257
  -2.500   0.3213   0.02959   0.02320  -0.0661   0.4482   0.0257
  -2.250   0.3200   0.02813   0.02154  -0.0605   0.4465   0.0256
  -2.000   0.3229   0.02705   0.02029  -0.0557   0.4449   0.0257
  -1.750   0.3261   0.02605   0.01911  -0.0510   0.4429   0.0258
  -1.500   0.3328   0.02526   0.01817  -0.0470   0.4413   0.0261
  -1.250   0.3395   0.02444   0.01717  -0.0430   0.4394   0.0263
  -1.000   0.3478   0.02368   0.01620  -0.0392   0.4375   0.0268
  -0.750   0.3598   0.02287   0.01520  -0.0362   0.4358   0.0268
  -0.500   0.3774   0.02193   0.01406  -0.0342   0.4342   0.0272
  -0.250   0.3987   0.02118   0.01314  -0.0331   0.4322   0.0275
   0.000   0.4233   0.02061   0.01238  -0.0327   0.4302   0.0279
   0.250   0.4404   0.02061   0.01237  -0.0312   0.4276   0.0284
   0.500   0.4593   0.02054   0.01226  -0.0301   0.4247   0.0286
   0.750   0.4779   0.02058   0.01226  -0.0289   0.4226   0.0288
   1.000   0.4952   0.02068   0.01231  -0.0276   0.4201   0.0291
   1.250   0.5184   0.02064   0.01223  -0.0274   0.4178   0.0294
   1.500   0.5419   0.02066   0.01225  -0.0273   0.4157   0.0298
   1.750   0.5648   0.02072   0.01229  -0.0271   0.4126   0.0304
   2.000   0.5896   0.02077   0.01231  -0.0274   0.4101   0.0308
   2.250   0.6115   0.02094   0.01244  -0.0273   0.4064   0.0311
   2.500   0.6305   0.02125   0.01269  -0.0267   0.4033   0.0316
   2.750   0.6562   0.02141   0.01286  -0.0274   0.4010   0.0318
   3.000   0.6789   0.02168   0.01317  -0.0275   0.3981   0.0325
   3.250   0.7012   0.02202   0.01352  -0.0277   0.3947   0.0330
   3.500   0.7221   0.02245   0.01396  -0.0278   0.3913   0.0337
   3.750   0.7430   0.02298   0.01445  -0.0281   0.3880   0.0349
   4.000   0.7669   0.02345   0.01492  -0.0288   0.3848   0.0355
   4.250   0.7896   0.02395   0.01545  -0.0294   0.3807   0.0364
   4.500   0.8078   0.02459   0.01611  -0.0294   0.3768   0.0373
   4.750   0.8237   0.02533   0.01683  -0.0290   0.3734   0.0382
   5.000   0.8403   0.02606   0.01754  -0.0288   0.3703   0.0390
   5.250   0.8586   0.02672   0.01824  -0.0287   0.3671   0.0404
   5.500   0.8747   0.02748   0.01901  -0.0284   0.3637   0.0414
   5.750   0.8868   0.02845   0.01998  -0.0276   0.3602   0.0428
   6.000   0.8978   0.02950   0.02101  -0.0269   0.3567   0.0446
   6.250   0.9124   0.03036   0.02191  -0.0264   0.3539   0.0470
   6.500   0.9261   0.03132   0.02288  -0.0260   0.3507   0.0496
   6.750   0.9383   0.03233   0.02391  -0.0254   0.3474   0.0514
   7.000   0.9472   0.03360   0.02518  -0.0246   0.3442   0.0550
   7.250   0.9547   0.03495   0.02652  -0.0237   0.3403   0.0603
   7.500   0.9686   0.03600   0.02767  -0.0235   0.3376   0.0901
   8.000   1.2556   0.04059   0.03428  -0.0778   0.3288   1.0000
   8.250   1.2593   0.04233   0.03601  -0.0766   0.3264   1.0000
   8.500   1.2653   0.04396   0.03765  -0.0756   0.3228   1.0000
   8.750   1.2706   0.04565   0.03936  -0.0746   0.3200   1.0000
   9.000   1.2755   0.04740   0.04112  -0.0737   0.3174   1.0000
   9.250   1.2786   0.04932   0.04304  -0.0726   0.3145   1.0000
   9.500   1.2806   0.05135   0.04506  -0.0716   0.3120   1.0000
   9.750   1.2850   0.05323   0.04695  -0.0708   0.3092   1.0000
  10.000   1.2905   0.05506   0.04881  -0.0701   0.3072   1.0000
  10.250   1.2983   0.05666   0.05043  -0.0696   0.3056   1.0000
  10.500   1.3019   0.05866   0.05246  -0.0688   0.3034   1.0000
  10.750   1.3048   0.06074   0.05455  -0.0681   0.3008   1.0000
  11.000   1.3105   0.06255   0.05635  -0.0676   0.2990   1.0000
  11.250   1.3126   0.06471   0.05850  -0.0668   0.2967   1.0000
  11.500   1.3171   0.06671   0.06053  -0.0663   0.2943   1.0000
  11.750   1.3258   0.06828   0.06213  -0.0660   0.2933   1.0000
  12.000   1.3292   0.07043   0.06433  -0.0656   0.2914   1.0000
  12.250   1.3336   0.07243   0.06636  -0.0651   0.2893   1.0000
  12.500   1.3359   0.07466   0.06859  -0.0647   0.2862   1.0000
  12.750   1.3372   0.07700   0.07093  -0.0642   0.2837   1.0000
  13.000   1.3402   0.07915   0.07307  -0.0637   0.2809   1.0000
  13.250   1.3503   0.08058   0.07453  -0.0636   0.2804   1.0000
  13.500   1.3553   0.08260   0.07660  -0.0634   0.2787   1.0000
  13.750   1.3573   0.08493   0.07898  -0.0631   0.2768   1.0000
  14.000   1.3610   0.08708   0.08116  -0.0629   0.2747   1.0000
  14.250   1.3662   0.08903   0.08314  -0.0627   0.2728   1.0000
  14.500   1.3730   0.09083   0.08495  -0.0626   0.2713   1.0000
  14.750   1.3777   0.09284   0.08696  -0.0625   0.2695   1.0000
  15.000   1.3844   0.09462   0.08873  -0.0624   0.2679   1.0000
  15.250   1.3932   0.09615   0.09029  -0.0625   0.2669   1.0000
  15.500   1.3964   0.09839   0.09260  -0.0624   0.2655   1.0000
  15.750   1.3991   0.10066   0.09493  -0.0623   0.2638   1.0000
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