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GOE 411 AIRFOIL (goe411-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 411 AIRFOIL (goe411-il)
Reynolds number: 1,000,000
Max Cl/Cd: 48.68 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe411-il-1000000.txt
Download as CSV file: xf-goe411-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 411 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.7000   0.08704   0.08492  -0.0438   1.0000   0.0079
 -13.250  -0.7131   0.08155   0.07936  -0.0469   1.0000   0.0079
 -13.000  -0.7329   0.07559   0.07330  -0.0502   1.0000   0.0079
 -12.750  -0.7494   0.07066   0.06826  -0.0525   1.0000   0.0079
 -12.500  -0.7714   0.06595   0.06342  -0.0543   1.0000   0.0079
 -12.250  -0.7921   0.06193   0.05927  -0.0548   1.0000   0.0079
 -12.000  -0.8104   0.05868   0.05589  -0.0541   1.0000   0.0079
 -11.750  -0.8219   0.05581   0.05293  -0.0528   1.0000   0.0079
 -11.500  -0.8404   0.05330   0.05029  -0.0501   1.0000   0.0079
 -11.250  -0.8665   0.05129   0.04811  -0.0453   1.0000   0.0080
 -11.000  -0.8840   0.04956   0.04627  -0.0404   1.0000   0.0080
 -10.750  -0.9074   0.04833   0.04492  -0.0333   1.0000   0.0080
 -10.500  -0.9212   0.04679   0.04328  -0.0275   1.0000   0.0080
 -10.250  -0.9356   0.04492   0.04126  -0.0216   1.0000   0.0080
 -10.000  -0.9469   0.04324   0.03941  -0.0160   1.0000   0.0080
  -9.750  -0.9521   0.04132   0.03735  -0.0113   1.0000   0.0080
  -9.500  -0.9606   0.03962   0.03545  -0.0058   1.0000   0.0080
  -8.750  -0.9139   0.02658   0.02171  -0.0035   0.9961   0.0073
  -8.500  -0.8859   0.02452   0.01946  -0.0043   0.9948   0.0073
  -8.250  -0.8573   0.02309   0.01790  -0.0050   0.9931   0.0075
  -8.000  -0.8301   0.02106   0.01574  -0.0053   0.9913   0.0074
  -7.750  -0.8030   0.01934   0.01394  -0.0056   0.9896   0.0074
  -7.500  -0.7738   0.01823   0.01274  -0.0064   0.9876   0.0076
  -7.250  -0.7432   0.01744   0.01189  -0.0074   0.9859   0.0079
  -7.000  -0.7197   0.01554   0.00992  -0.0074   0.9841   0.0084
  -6.750  -0.6934   0.01449   0.00884  -0.0078   0.9819   0.0090
  -6.500  -0.6711   0.01386   0.00817  -0.0070   0.9771   0.0094
  -6.250  -0.6417   0.01323   0.00750  -0.0077   0.9744   0.0100
  -6.000  -0.6107   0.01259   0.00680  -0.0087   0.9725   0.0106
  -5.750  -0.5773   0.01218   0.00637  -0.0103   0.9712   0.0115
  -5.500  -0.5438   0.01174   0.00590  -0.0117   0.9701   0.0121
  -5.250  -0.5241   0.01107   0.00513  -0.0101   0.9645   0.0130
  -5.000  -0.4956   0.01050   0.00449  -0.0105   0.9614   0.0147
  -4.750  -0.4622   0.01011   0.00405  -0.0119   0.9593   0.0164
  -4.500  -0.4263   0.00980   0.00372  -0.0139   0.9576   0.0182
  -4.250  -0.3907   0.00944   0.00331  -0.0157   0.9558   0.0252
  -4.000  -0.3802   0.00821   0.00270  -0.0126   0.9461   0.1729
  -3.750  -0.3505   0.00749   0.00235  -0.0136   0.9421   0.2540
  -3.500  -0.3321   0.00695   0.00212  -0.0119   0.9324   0.3293
  -3.250  -0.3043   0.00654   0.00192  -0.0122   0.9253   0.3882
  -3.000  -0.2783   0.00627   0.00178  -0.0119   0.9159   0.4307
  -2.750  -0.2528   0.00606   0.00167  -0.0115   0.9052   0.4652
  -2.500  -0.2260   0.00591   0.00157  -0.0114   0.8940   0.4912
  -2.250  -0.1994   0.00580   0.00148  -0.0112   0.8816   0.5123
  -2.000  -0.1730   0.00573   0.00140  -0.0109   0.8681   0.5256
  -1.750  -0.1476   0.00569   0.00133  -0.0104   0.8531   0.5384
  -1.500  -0.1232   0.00566   0.00127  -0.0096   0.8345   0.5510
  -1.250  -0.0997   0.00564   0.00122  -0.0086   0.8157   0.5660
  -1.000  -0.0774   0.00561   0.00118  -0.0074   0.7953   0.5838
  -0.750  -0.0556   0.00561   0.00114  -0.0061   0.7717   0.5989
  -0.500  -0.0348   0.00562   0.00110  -0.0046   0.7417   0.6141
  -0.250  -0.0166   0.00567   0.00107  -0.0024   0.6993   0.6318
   0.000  -0.0001   0.00572   0.00105   0.0000   0.6573   0.6579
   0.250   0.0167   0.00567   0.00107   0.0024   0.6317   0.6983
   0.500   0.0346   0.00561   0.00110   0.0046   0.6140   0.7431
   0.750   0.0555   0.00561   0.00114   0.0061   0.5988   0.7722
   1.000   0.0773   0.00561   0.00118   0.0075   0.5832   0.7951
   1.500   0.1231   0.00566   0.00127   0.0096   0.5506   0.8349
   1.750   0.1476   0.00569   0.00133   0.0104   0.5380   0.8524
   2.000   0.1730   0.00573   0.00140   0.0109   0.5256   0.8680
   2.250   0.1992   0.00580   0.00148   0.0112   0.5110   0.8816
   2.500   0.2260   0.00591   0.00157   0.0114   0.4911   0.8940
   2.750   0.2528   0.00606   0.00167   0.0115   0.4649   0.9051
   3.000   0.2781   0.00627   0.00178   0.0120   0.4302   0.9158
   3.250   0.3041   0.00655   0.00192   0.0122   0.3864   0.9253
   3.500   0.3320   0.00695   0.00212   0.0119   0.3294   0.9324
   3.750   0.3512   0.00743   0.00233   0.0135   0.2629   0.9420
   4.000   0.3806   0.00819   0.00270   0.0125   0.1761   0.9461
   4.250   0.3910   0.00943   0.00331   0.0156   0.0259   0.9558
   4.500   0.4266   0.00980   0.00371   0.0138   0.0183   0.9576
   4.750   0.4620   0.01012   0.00407   0.0119   0.0161   0.9593
   5.000   0.4956   0.01051   0.00449   0.0105   0.0144   0.9614
   5.250   0.5242   0.01107   0.00512   0.0101   0.0130   0.9644
   5.500   0.5442   0.01169   0.00584   0.0117   0.0120   0.9701
   5.750   0.5776   0.01215   0.00634   0.0102   0.0113   0.9712
   6.000   0.6106   0.01259   0.00680   0.0088   0.0102   0.9725
   6.250   0.6417   0.01322   0.00748   0.0077   0.0099   0.9744
   6.500   0.6718   0.01380   0.00808   0.0068   0.0092   0.9770
   6.750   0.6943   0.01446   0.00879   0.0076   0.0088   0.9818
   7.000   0.7206   0.01545   0.00983   0.0073   0.0086   0.9840
   7.250   0.7408   0.01796   0.01239   0.0078   0.0080   0.9858
   7.500   0.7709   0.01902   0.01351   0.0068   0.0079   0.9874
   7.750   0.8029   0.01933   0.01393   0.0057   0.0073   0.9895
   8.000   0.8303   0.02105   0.01573   0.0053   0.0074   0.9913
   8.250   0.8572   0.02325   0.01807   0.0050   0.0075   0.9930
   8.500   0.8863   0.02429   0.01923   0.0043   0.0072   0.9948
   8.750   0.9133   0.02697   0.02212   0.0037   0.0074   0.9961
   9.250   0.9500   0.03703   0.03263   0.0042   0.0080   0.9987
   9.500   0.9605   0.03968   0.03551   0.0058   0.0080   1.0000
   9.750   0.9550   0.04137   0.03737   0.0108   0.0080   1.0000
  10.000   0.9492   0.04326   0.03941   0.0156   0.0080   1.0000
  10.250   0.9353   0.04508   0.04141   0.0217   0.0080   1.0000
  10.500   0.9258   0.04685   0.04331   0.0267   0.0080   1.0000
  10.750   0.8947   0.04789   0.04453   0.0356   0.0079   1.0000
  11.000   0.8894   0.04966   0.04635   0.0395   0.0080   1.0000
  11.250   0.8670   0.05133   0.04815   0.0453   0.0080   1.0000
  11.500   0.8427   0.05331   0.05030   0.0499   0.0079   1.0000
  11.750   0.8251   0.05581   0.05292   0.0525   0.0079   1.0000
  12.000   0.8048   0.05888   0.05613   0.0542   0.0079   1.0000
  12.250   0.7913   0.06211   0.05945   0.0547   0.0079   1.0000
  12.500   0.7755   0.06587   0.06332   0.0544   0.0079   1.0000
  12.750   0.7567   0.07020   0.06777   0.0530   0.0079   1.0000
  13.000   0.7317   0.07585   0.07357   0.0499   0.0079   1.0000
  13.250   0.7157   0.08129   0.07910   0.0470   0.0079   1.0000
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