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GOE 548 AIRFOIL (goe548-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 548 AIRFOIL (goe548-il)
Reynolds number: 1,000,000
Max Cl/Cd: 100.74 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe548-il-1000000.txt
Download as CSV file: xf-goe548-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 548 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
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.6942   0.08203   0.08030  -0.0539   1.0000   0.0074
 -13.500  -0.8405   0.04954   0.04722  -0.0748   1.0000   0.0066
 -13.250  -0.8607   0.04386   0.04139  -0.0780   1.0000   0.0066
 -13.000  -0.8854   0.03919   0.03656  -0.0789   1.0000   0.0066
 -12.500  -0.8934   0.03438   0.03155  -0.0794   0.9982   0.0068
 -12.250  -0.8917   0.03075   0.02763  -0.0816   0.9947   0.0068
 -12.000  -0.8827   0.02883   0.02554  -0.0815   0.9904   0.0069
 -11.750  -0.8680   0.02700   0.02352  -0.0818   0.9867   0.0070
 -11.500  -0.8476   0.02512   0.02144  -0.0829   0.9846   0.0072
 -11.250  -0.8289   0.02400   0.02020  -0.0827   0.9811   0.0074
 -11.000  -0.8118   0.02249   0.01850  -0.0822   0.9772   0.0076
 -10.750  -0.7891   0.02131   0.01718  -0.0826   0.9751   0.0079
 -10.500  -0.7652   0.02010   0.01581  -0.0830   0.9735   0.0081
 -10.250  -0.7392   0.01909   0.01467  -0.0837   0.9724   0.0083
 -10.000  -0.7110   0.01832   0.01378  -0.0846   0.9715   0.0085
  -9.750  -0.6999   0.01669   0.01192  -0.0824   0.9656   0.0090
  -9.500  -0.6752   0.01569   0.01085  -0.0826   0.9634   0.0097
  -9.250  -0.6463   0.01511   0.01021  -0.0835   0.9619   0.0102
  -9.000  -0.6165   0.01449   0.00952  -0.0845   0.9607   0.0107
  -8.750  -0.5861   0.01385   0.00879  -0.0856   0.9594   0.0113
  -8.500  -0.5561   0.01329   0.00815  -0.0865   0.9577   0.0117
  -8.250  -0.5365   0.01259   0.00734  -0.0852   0.9533   0.0123
  -8.000  -0.5119   0.01192   0.00661  -0.0850   0.9503   0.0135
  -7.750  -0.4825   0.01154   0.00619  -0.0857   0.9481   0.0147
  -7.500  -0.4515   0.01117   0.00577  -0.0867   0.9460   0.0158
  -7.250  -0.4260   0.01067   0.00522  -0.0865   0.9428   0.0178
  -7.000  -0.4015   0.01042   0.00496  -0.0860   0.9391   0.0199
  -6.750  -0.3746   0.01016   0.00466  -0.0860   0.9359   0.0221
  -6.500  -0.3461   0.00985   0.00438  -0.0864   0.9331   0.0266
  -6.250  -0.3153   0.00971   0.00420  -0.0872   0.9307   0.0295
  -6.000  -0.2929   0.00947   0.00400  -0.0862   0.9270   0.0339
  -5.750  -0.2665   0.00937   0.00388  -0.0860   0.9237   0.0366
  -5.500  -0.2383   0.00930   0.00378  -0.0862   0.9204   0.0379
  -5.250  -0.2112   0.00893   0.00335  -0.0862   0.9168   0.0425
  -5.000  -0.1881   0.00876   0.00317  -0.0853   0.9124   0.0454
  -4.750  -0.1626   0.00860   0.00297  -0.0848   0.9073   0.0477
  -4.250  -0.1119   0.00826   0.00255  -0.0838   0.8960   0.0547
  -4.000  -0.0865   0.00806   0.00233  -0.0833   0.8904   0.0601
  -3.750  -0.0615   0.00787   0.00215  -0.0828   0.8853   0.0711
  -3.500  -0.0422   0.00732   0.00192  -0.0812   0.8792   0.1494
  -3.250  -0.0188   0.00693   0.00176  -0.0805   0.8738   0.2218
  -3.000   0.0025   0.00664   0.00164  -0.0792   0.8670   0.2713
  -2.750   0.0261   0.00636   0.00152  -0.0784   0.8605   0.3250
  -2.500   0.0487   0.00613   0.00143  -0.0774   0.8525   0.3742
  -2.250   0.0730   0.00595   0.00134  -0.0767   0.8443   0.4129
  -2.000   0.0959   0.00577   0.00126  -0.0757   0.8328   0.4520
  -1.750   0.1188   0.00560   0.00119  -0.0746   0.8190   0.4941
  -1.500   0.1412   0.00546   0.00112  -0.0734   0.8016   0.5373
  -1.250   0.1630   0.00540   0.00106  -0.0721   0.7801   0.5721
  -1.000   0.1848   0.00539   0.00103  -0.0708   0.7616   0.6025
  -0.500   0.2296   0.00535   0.00105  -0.0684   0.7348   0.6655
  -0.250   0.2512   0.00527   0.00108  -0.0670   0.7255   0.7136
   0.000   0.2731   0.00524   0.00111  -0.0657   0.7154   0.7518
   0.250   0.2960   0.00521   0.00115  -0.0645   0.7062   0.7841
   0.500   0.3199   0.00519   0.00119  -0.0636   0.6990   0.8114
   1.000   0.3689   0.00518   0.00128  -0.0621   0.6846   0.8593
   1.250   0.3943   0.00517   0.00133  -0.0614   0.6760   0.8850
   1.500   0.4229   0.00518   0.00140  -0.0616   0.6663   0.9120
   1.750   0.4599   0.00525   0.00150  -0.0636   0.6542   0.9350
   2.000   0.4992   0.00536   0.00159  -0.0662   0.6412   0.9482
   2.250   0.5346   0.00548   0.00168  -0.0680   0.6235   0.9572
   2.500   0.5702   0.00566   0.00177  -0.0698   0.5949   0.9634
   2.750   0.5975   0.00599   0.00190  -0.0699   0.5491   0.9712
   3.000   0.6274   0.00644   0.00211  -0.0706   0.4981   0.9763
   3.250   0.6544   0.00679   0.00230  -0.0706   0.4588   0.9831
   3.500   0.6885   0.00716   0.00248  -0.0723   0.4154   0.9860
   3.750   0.7181   0.00778   0.00276  -0.0732   0.3394   0.9903
   4.000   0.7412   0.00896   0.00328  -0.0732   0.2026   0.9954
   4.250   0.7750   0.00954   0.00360  -0.0750   0.1514   0.9985
   4.500   0.7983   0.01017   0.00392  -0.0747   0.0916   1.0000
   4.750   0.8115   0.01048   0.00415  -0.0718   0.0750   1.0000
   5.000   0.8182   0.01111   0.00453  -0.0677   0.0240   1.0000
   5.250   0.8328   0.01142   0.00485  -0.0650   0.0179   1.0000
   5.500   0.8495   0.01165   0.00511  -0.0628   0.0168   1.0000
   5.750   0.8657   0.01192   0.00540  -0.0605   0.0155   1.0000
   6.000   0.8811   0.01224   0.00576  -0.0580   0.0146   1.0000
   6.250   0.8930   0.01275   0.00633  -0.0548   0.0130   1.0000
   6.500   0.9051   0.01317   0.00680  -0.0517   0.0127   1.0000
   6.750   0.9192   0.01345   0.00710  -0.0490   0.0122   1.0000
   7.000   0.9327   0.01378   0.00747  -0.0462   0.0116   1.0000
   7.250   0.9452   0.01422   0.00796  -0.0432   0.0114   1.0000
   7.500   0.9593   0.01464   0.00841  -0.0407   0.0107   1.0000
   7.750   0.9722   0.01516   0.00896  -0.0380   0.0103   1.0000
   8.000   0.9864   0.01563   0.00946  -0.0357   0.0098   1.0000
   8.250   0.9905   0.01671   0.01060  -0.0317   0.0092   1.0000
   8.500   0.9956   0.01783   0.01179  -0.0279   0.0089   1.0000
   8.750   1.0120   0.01829   0.01230  -0.0262   0.0087   1.0000
   9.000   1.0253   0.01898   0.01305  -0.0240   0.0086   1.0000
   9.250   1.0390   0.01969   0.01380  -0.0219   0.0082   1.0000
   9.500   1.0516   0.02050   0.01467  -0.0197   0.0080   1.0000
   9.750   1.0632   0.02146   0.01569  -0.0175   0.0079   1.0000
  10.000   1.0766   0.02227   0.01656  -0.0156   0.0077   1.0000
  10.250   1.0882   0.02336   0.01770  -0.0136   0.0075   1.0000
  10.500   1.1014   0.02421   0.01860  -0.0118   0.0072   1.0000
  10.750   1.1136   0.02517   0.01963  -0.0101   0.0070   1.0000
  11.000   1.1253   0.02612   0.02062  -0.0084   0.0067   1.0000
  11.250   1.1362   0.02748   0.02206  -0.0065   0.0067   1.0000
  11.500   1.1471   0.02890   0.02355  -0.0047   0.0066   1.0000
  11.750   1.1602   0.03276   0.02758  -0.0033   0.0062   1.0000
  12.000   1.1653   0.03383   0.02876  -0.0010   0.0061   1.0000
  12.250   1.1692   0.03442   0.02947   0.0011   0.0059   1.0000
  12.500   1.1737   0.03660   0.03182   0.0032   0.0059   1.0000
  12.750   1.1770   0.03846   0.03382   0.0051   0.0058   1.0000
  13.000   1.1780   0.04055   0.03607   0.0070   0.0057   1.0000
  13.250   1.1742   0.04346   0.03916   0.0090   0.0058   1.0000
  13.500   1.1674   0.04662   0.04251   0.0109   0.0059   1.0000
  13.750   1.1620   0.04924   0.04530   0.0122   0.0057   1.0000
  14.000   1.1502   0.05295   0.04921   0.0133   0.0057   1.0000
  14.250   1.1383   0.05676   0.05319   0.0140   0.0057   1.0000
  14.500   1.1226   0.06120   0.05781   0.0141   0.0057   1.0000
  14.750   1.1126   0.06508   0.06185   0.0137   0.0056   1.0000
  15.000   1.0988   0.06977   0.06670   0.0127   0.0055   1.0000
  15.250   1.0717   0.07687   0.07398   0.0108   0.0058   1.0000
  15.500   1.0613   0.08186   0.07911   0.0086   0.0056   1.0000
  16.000   1.0133   0.09754   0.09508   0.0011   0.0059   1.0000
  16.250   0.9945   0.10545   0.10314  -0.0034   0.0059   1.0000
  16.500   0.9769   0.11360   0.11142  -0.0083   0.0058   1.0000
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