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GOE 460 AIRFOIL (goe460-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 460 AIRFOIL (goe460-il)
Reynolds number: 50,000
Max Cl/Cd: 20.79 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe460-il-50000.txt
Download as CSV file: xf-goe460-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 460 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.2982   0.12267   0.11336  -0.0184   1.0000   0.4841
 -10.750  -0.2755   0.11935   0.11001  -0.0187   1.0000   0.4919
 -10.500  -0.2992   0.11916   0.10987  -0.0165   1.0000   0.5009
 -10.250  -0.2706   0.11479   0.10547  -0.0174   1.0000   0.5071
 -10.000  -0.3613   0.10474   0.09541  -0.0206   1.0000   0.4225
  -9.750  -0.3604   0.10095   0.09162  -0.0205   1.0000   0.4195
  -9.500  -0.3710   0.09700   0.08767  -0.0201   1.0000   0.4178
  -9.250  -0.3894   0.09312   0.08381  -0.0191   1.0000   0.4199
  -9.000  -0.4244   0.08835   0.07909  -0.0176   1.0000   0.4228
  -8.750  -0.3907   0.08846   0.07919  -0.0161   1.0000   0.4334
  -8.500  -0.4108   0.08510   0.07586  -0.0142   1.0000   0.4384
  -8.250  -0.4622   0.07973   0.07057  -0.0112   1.0000   0.4422
  -8.000  -0.4190   0.08093   0.07174  -0.0099   1.0000   0.4523
  -7.750  -0.4505   0.07738   0.06825  -0.0067   1.0000   0.4584
  -7.500  -0.5754   0.06724   0.05827   0.0000   1.0000   0.4625
  -7.250  -0.7731   0.05462   0.04584   0.0172   1.0000   0.4646
  -7.000  -0.5731   0.06548   0.05655   0.0063   1.0000   0.4804
  -6.750  -0.8460   0.04951   0.04071   0.0320   1.0000   0.4797
  -6.500  -0.6417   0.05914   0.05032   0.0167   1.0000   0.4973
  -6.250  -0.8631   0.04711   0.03828   0.0414   1.0000   0.4992
  -6.000  -0.7941   0.04994   0.04121   0.0381   1.0000   0.5117
  -5.750  -0.8870   0.04431   0.03540   0.0517   1.0000   0.5207
  -5.500  -0.8262   0.04659   0.03783   0.0487   1.0000   0.5321
  -5.250  -0.8598   0.04389   0.03504   0.0560   1.0000   0.5434
  -5.000  -0.8435   0.04377   0.03494   0.0577   1.0000   0.5545
  -4.750  -0.8412   0.04291   0.03407   0.0610   1.0000   0.5666
  -4.500  -0.8563   0.04125   0.03233   0.0663   1.0000   0.5813
  -4.250  -0.8283   0.04191   0.03306   0.0667   1.0000   0.5945
  -4.000  -0.8145   0.04184   0.03301   0.0687   1.0000   0.6085
  -3.750  -0.8120   0.04119   0.03234   0.0721   1.0000   0.6241
  -3.500  -0.8119   0.04049   0.03160   0.0757   1.0000   0.6407
  -3.250  -0.7815   0.04153   0.03269   0.0757   1.0000   0.6546
  -3.000  -0.7589   0.04220   0.03339   0.0765   1.0000   0.6693
  -2.750  -0.7462   0.04237   0.03355   0.0786   1.0000   0.6850
  -2.500  -0.6693   0.04489   0.03601   0.0700   0.9844   0.7032
  -2.250  -0.6108   0.04652   0.03757   0.0642   0.9703   0.7205
  -2.000  -0.5317   0.04901   0.03999   0.0558   0.9562   0.7349
  -1.750  -0.4185   0.05228   0.04321   0.0423   0.9417   0.7459
  -1.500  -0.3556   0.05352   0.04438   0.0358   0.9294   0.7614
  -1.250  -0.3305   0.05371   0.04454   0.0350   0.9170   0.7781
  -1.000  -0.2163   0.05628   0.04709   0.0215   0.9027   0.7902
  -0.750  -0.1457   0.05733   0.04812   0.0139   0.8902   0.8071
  -0.500  -0.0776   0.05787   0.04865   0.0065   0.8780   0.8245
  -0.250  -0.0674   0.05787   0.04864   0.0077   0.8649   0.8393
   0.000   0.0000   0.05811   0.04888   0.0000   0.8522   0.8523
   0.250   0.0673   0.05787   0.04864  -0.0077   0.8393   0.8649
   0.500   0.0772   0.05787   0.04864  -0.0065   0.8244   0.8779
   0.750   0.1450   0.05734   0.04813  -0.0139   0.8073   0.8902
   1.000   0.2162   0.05628   0.04709  -0.0215   0.7904   0.9027
   1.250   0.3303   0.05370   0.04453  -0.0350   0.7781   0.9170
   1.500   0.3558   0.05350   0.04437  -0.0358   0.7614   0.9295
   1.750   0.4197   0.05222   0.04314  -0.0425   0.7458   0.9418
   2.000   0.5307   0.04902   0.04000  -0.0557   0.7346   0.9563
   2.250   0.6115   0.04648   0.03753  -0.0643   0.7205   0.9705
   2.500   0.6683   0.04493   0.03605  -0.0699   0.7033   0.9844
   2.750   0.7443   0.04244   0.03362  -0.0783   0.6852   0.9998
   3.000   0.7587   0.04219   0.03339  -0.0765   0.6694   1.0000
   3.250   0.7819   0.04150   0.03266  -0.0758   0.6549   1.0000
   3.500   0.8116   0.04049   0.03159  -0.0757   0.6408   1.0000
   3.750   0.8123   0.04115   0.03229  -0.0721   0.6241   1.0000
   4.000   0.8145   0.04182   0.03299  -0.0687   0.6085   1.0000
   4.250   0.8284   0.04188   0.03303  -0.0667   0.5945   1.0000
   4.500   0.8566   0.04120   0.03227  -0.0664   0.5812   1.0000
   4.750   0.8406   0.04293   0.03408  -0.0609   0.5667   1.0000
   5.000   0.8437   0.04373   0.03490  -0.0577   0.5546   1.0000
   5.250   0.8605   0.04382   0.03497  -0.0561   0.5433   1.0000
   5.500   0.8262   0.04658   0.03782  -0.0487   0.5323   1.0000
   5.750   0.8872   0.04430   0.03538  -0.0517   0.5208   1.0000
   6.000   0.7944   0.04991   0.04118  -0.0382   0.5118   1.0000
   6.250   0.8639   0.04706   0.03823  -0.0415   0.4993   1.0000
   6.500   0.6487   0.05872   0.04990  -0.0172   0.4972   1.0000
   6.750   0.8453   0.04950   0.04070  -0.0319   0.4796   1.0000
   7.000   0.5770   0.06516   0.05623  -0.0065   0.4804   1.0000
   7.250   0.4591   0.07422   0.06515   0.0011   0.4752   1.0000
   7.500   0.5795   0.06689   0.05793  -0.0002   0.4626   1.0000
   7.750   0.4513   0.07728   0.06814   0.0067   0.4584   1.0000
   8.000   0.4184   0.08095   0.07175   0.0099   0.4527   1.0000
   8.250   0.4636   0.07961   0.07044   0.0112   0.4423   1.0000
   8.500   0.4116   0.08500   0.07576   0.0142   0.4385   1.0000
   8.750   0.3923   0.08827   0.07899   0.0162   0.4329   1.0000
   9.000   0.4250   0.08828   0.07901   0.0176   0.4228   1.0000
   9.250   0.3891   0.09303   0.08372   0.0192   0.4195   1.0000
   9.500   0.3713   0.09691   0.08758   0.0201   0.4175   1.0000
   9.750   0.3605   0.10086   0.09152   0.0205   0.4192   1.0000
  10.000   0.3600   0.10467   0.09534   0.0206   0.4222   1.0000
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