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GOE 416A AIRFOIL (goe416a-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 416A AIRFOIL (goe416a-il)
Reynolds number: 100,000
Max Cl/Cd: 46.45 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe416a-il-100000.txt
Download as CSV file: xf-goe416a-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 416A AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4393   0.11453   0.10995  -0.0062   1.0000   0.1597
 -10.500  -0.4673   0.11115   0.10665  -0.0099   1.0000   0.1679
 -10.250  -0.6068   0.11445   0.10977  -0.0016   1.0000   0.1553
 -10.000  -0.5782   0.11200   0.10727   0.0025   1.0000   0.1655
  -9.750  -0.5720   0.10830   0.10357   0.0025   1.0000   0.1736
  -9.500  -0.5819   0.10423   0.09959  -0.0003   1.0000   0.1842
  -9.250  -0.6113   0.10060   0.09610  -0.0065   1.0000   0.1960
  -9.000  -0.5876   0.09790   0.09336  -0.0030   1.0000   0.2095
  -7.000  -0.6287   0.03725   0.02948  -0.0391   1.0000   0.0726
  -6.750  -0.6070   0.03367   0.02567  -0.0382   1.0000   0.0684
  -6.500  -0.5826   0.03174   0.02302  -0.0366   1.0000   0.0626
  -6.250  -0.5577   0.02957   0.02069  -0.0355   1.0000   0.0598
  -6.000  -0.5336   0.02716   0.01817  -0.0343   1.0000   0.0573
  -5.750  -0.5093   0.02531   0.01620  -0.0330   1.0000   0.0554
  -5.500  -0.4857   0.02377   0.01460  -0.0315   1.0000   0.0543
  -5.250  -0.4634   0.02243   0.01329  -0.0301   1.0000   0.0541
  -5.000  -0.4426   0.02126   0.01218  -0.0286   1.0000   0.0550
  -4.750  -0.4223   0.02030   0.01121  -0.0273   1.0000   0.0582
  -4.500  -0.4014   0.01947   0.01031  -0.0261   1.0000   0.0608
  -4.250  -0.3802   0.01846   0.00920  -0.0252   1.0000   0.0634
  -4.000  -0.3576   0.01762   0.00824  -0.0246   1.0000   0.0688
  -3.750  -0.3339   0.01678   0.00738  -0.0241   1.0000   0.0827
  -3.500  -0.3136   0.01486   0.00737  -0.0243   1.0000   0.4762
  -3.250  -0.2948   0.01588   0.00843  -0.0215   1.0000   0.5392
  -3.000  -0.2768   0.01667   0.00925  -0.0187   1.0000   0.5786
  -2.750  -0.2602   0.01723   0.00993  -0.0156   1.0000   0.6088
  -2.500  -0.2421   0.01749   0.01023  -0.0134   1.0000   0.6283
  -2.250  -0.2275   0.01790   0.01075  -0.0101   1.0000   0.6564
  -2.000  -0.2092   0.01805   0.01091  -0.0084   1.0000   0.6745
  -1.750  -0.1863   0.01802   0.01081  -0.0084   1.0000   0.6834
  -1.500  -0.1499   0.01803   0.01070  -0.0112   0.9950   0.6920
  -1.250  -0.0990   0.01795   0.01053  -0.0165   0.9837   0.6982
  -1.000  -0.0498   0.01785   0.01035  -0.0214   0.9715   0.7044
  -0.750  -0.0015   0.01771   0.01013  -0.0262   0.9589   0.7100
  -0.500   0.0451   0.01755   0.00996  -0.0302   0.9464   0.7152
  -0.250   0.0934   0.01736   0.00973  -0.0346   0.9343   0.7209
   0.000   0.1372   0.01713   0.00951  -0.0378   0.9212   0.7259
   0.250   0.1772   0.01689   0.00929  -0.0399   0.9064   0.7313
   0.500   0.2144   0.01663   0.00902  -0.0415   0.8894   0.7369
   0.750   0.2465   0.01634   0.00877  -0.0416   0.8717   0.7420
   1.000   0.2771   0.01607   0.00851  -0.0414   0.8540   0.7481
   1.250   0.3040   0.01589   0.00835  -0.0407   0.8329   0.7538
   1.500   0.3305   0.01567   0.00815  -0.0397   0.8131   0.7599
   1.750   0.3570   0.01551   0.00797  -0.0389   0.7924   0.7672
   2.000   0.3821   0.01535   0.00783  -0.0377   0.7706   0.7744
   2.250   0.4086   0.01525   0.00774  -0.0369   0.7506   0.7824
   2.500   0.4346   0.01523   0.00776  -0.0362   0.7301   0.7913
   2.750   0.4608   0.01521   0.00776  -0.0355   0.7112   0.8016
   3.000   0.4868   0.01524   0.00782  -0.0348   0.6918   0.8138
   3.250   0.5123   0.01527   0.00796  -0.0340   0.6719   0.8284
   3.500   0.5374   0.01530   0.00806  -0.0331   0.6535   0.8469
   3.750   0.5622   0.01531   0.00820  -0.0320   0.6355   0.8754
   4.000   0.5954   0.01529   0.00842  -0.0328   0.6136   0.9400
   4.250   0.6318   0.01549   0.00856  -0.0350   0.5896   1.0000
   4.500   0.6615   0.01573   0.00869  -0.0356   0.5643   1.0000
   4.750   0.6892   0.01593   0.00883  -0.0356   0.5361   1.0000
   5.000   0.7159   0.01618   0.00906  -0.0353   0.5078   1.0000
   5.250   0.7420   0.01650   0.00930  -0.0349   0.4787   1.0000
   5.500   0.7667   0.01687   0.00958  -0.0342   0.4455   1.0000
   5.750   0.7908   0.01728   0.00992  -0.0335   0.4111   1.0000
   6.000   0.8148   0.01772   0.01034  -0.0329   0.3788   1.0000
   6.250   0.8385   0.01812   0.01074  -0.0322   0.3450   1.0000
   6.500   0.8612   0.01854   0.01114  -0.0314   0.3063   1.0000
   6.750   0.8814   0.01932   0.01175  -0.0304   0.2583   1.0000
   7.000   0.8976   0.02081   0.01294  -0.0290   0.1980   1.0000
   7.250   0.9146   0.02220   0.01402  -0.0277   0.1410   1.0000
   7.500   0.9295   0.02414   0.01559  -0.0262   0.1102   1.0000
   7.750   0.9467   0.02604   0.01744  -0.0248   0.0887   1.0000
   8.000   0.9655   0.02810   0.01945  -0.0235   0.0755   1.0000
   8.250   0.9855   0.03013   0.02153  -0.0224   0.0658   1.0000
   8.500   1.0077   0.03298   0.02424  -0.0218   0.0596   1.0000
   8.750   1.0293   0.03532   0.02703  -0.0205   0.0561   1.0000
   9.000   1.0483   0.03752   0.02944  -0.0195   0.0518   1.0000
   9.250   1.0666   0.04140   0.03335  -0.0190   0.0486   1.0000
   9.500   1.0785   0.04501   0.03744  -0.0174   0.0478   1.0000
   9.750   1.0862   0.04859   0.04153  -0.0155   0.0474   1.0000
  10.000   1.0892   0.05261   0.04602  -0.0136   0.0473   1.0000
  10.250   1.0876   0.05689   0.05070  -0.0117   0.0474   1.0000
  10.500   1.0810   0.06114   0.05531  -0.0098   0.0475   1.0000
  10.750   1.0696   0.06535   0.05983  -0.0081   0.0476   1.0000
  11.000   1.0532   0.06939   0.06410  -0.0062   0.0478   1.0000
  11.250   1.0363   0.07403   0.06892  -0.0056   0.0480   1.0000
  11.750   0.9419   0.08967   0.08537  -0.0166   0.0525   1.0000
  12.000   0.8938   0.10421   0.10002  -0.0282   0.0549   1.0000
  12.250   0.8675   0.11637   0.11211  -0.0356   0.0574   1.0000
  12.500   0.8616   0.12302   0.11873  -0.0378   0.0589   1.0000
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