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GOE 623 AIRFOIL (goe623-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 623 AIRFOIL (goe623-il)
Reynolds number: 500,000
Max Cl/Cd: 91.27 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe623-il-500000-n5.txt
Download as CSV file: xf-goe623-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 623 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
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.7254   0.07605   0.07353  -0.0474   1.0000   0.0133
 -13.000  -0.9052   0.03709   0.03393  -0.0804   1.0000   0.0121
 -12.750  -0.9112   0.03398   0.03060  -0.0799   1.0000   0.0123
 -12.500  -0.9115   0.03162   0.02802  -0.0784   1.0000   0.0126
 -12.250  -0.9089   0.02965   0.02585  -0.0765   1.0000   0.0128
 -12.000  -0.9032   0.02793   0.02391  -0.0745   0.9998   0.0131
 -11.750  -0.8761   0.02671   0.02262  -0.0760   0.9964   0.0135
 -11.500  -0.8468   0.02587   0.02170  -0.0774   0.9933   0.0139
 -11.250  -0.8170   0.02508   0.02082  -0.0788   0.9887   0.0144
 -11.000  -0.7861   0.02421   0.01983  -0.0804   0.9836   0.0150
 -10.750  -0.7575   0.02317   0.01863  -0.0816   0.9758   0.0157
 -10.500  -0.7301   0.02201   0.01723  -0.0825   0.9669   0.0164
 -10.250  -0.7016   0.02116   0.01627  -0.0834   0.9576   0.0169
 -10.000  -0.6721   0.02067   0.01571  -0.0842   0.9481   0.0174
  -9.750  -0.6450   0.02018   0.01515  -0.0844   0.9378   0.0179
  -9.500  -0.6186   0.01965   0.01450  -0.0845   0.9285   0.0185
  -9.250  -0.5931   0.01909   0.01381  -0.0843   0.9188   0.0193
  -9.000  -0.5680   0.01852   0.01306  -0.0840   0.9097   0.0201
  -8.500  -0.5186   0.01726   0.01154  -0.0833   0.8927   0.0214
  -8.000  -0.4673   0.01643   0.01056  -0.0828   0.8773   0.0226
  -7.750  -0.4414   0.01605   0.01007  -0.0825   0.8698   0.0234
  -7.500  -0.4152   0.01561   0.00952  -0.0823   0.8627   0.0242
  -7.250  -0.3890   0.01518   0.00897  -0.0820   0.8558   0.0250
  -7.000  -0.3623   0.01484   0.00853  -0.0818   0.8490   0.0256
  -6.750  -0.3361   0.01435   0.00792  -0.0815   0.8415   0.0262
  -6.500  -0.3107   0.01368   0.00718  -0.0812   0.8346   0.0271
  -6.250  -0.2842   0.01324   0.00670  -0.0810   0.8272   0.0278
  -6.000  -0.2574   0.01290   0.00628  -0.0809   0.8205   0.0286
  -5.750  -0.2303   0.01255   0.00588  -0.0807   0.8130   0.0294
  -5.500  -0.2034   0.01223   0.00547  -0.0805   0.8055   0.0301
  -5.250  -0.1761   0.01190   0.00509  -0.0804   0.7970   0.0307
  -5.000  -0.1488   0.01164   0.00474  -0.0802   0.7886   0.0314
  -4.750  -0.1212   0.01141   0.00444  -0.0801   0.7795   0.0321
  -4.500  -0.0939   0.01112   0.00409  -0.0799   0.7708   0.0327
  -4.250  -0.0666   0.01082   0.00372  -0.0798   0.7606   0.0337
  -4.000  -0.0391   0.01058   0.00343  -0.0797   0.7496   0.0347
  -3.750  -0.0115   0.01040   0.00318  -0.0795   0.7375   0.0358
  -3.500   0.0161   0.01024   0.00296  -0.0794   0.7245   0.0371
  -3.250   0.0437   0.01012   0.00275  -0.0793   0.7110   0.0387
  -3.000   0.0714   0.01000   0.00257  -0.0792   0.6972   0.0411
  -2.750   0.0989   0.00987   0.00241  -0.0790   0.6833   0.0469
  -2.500   0.1262   0.00969   0.00226  -0.0789   0.6697   0.0684
  -2.250   0.1535   0.00954   0.00214  -0.0788   0.6574   0.0909
  -2.000   0.1810   0.00943   0.00209  -0.0788   0.6468   0.1223
  -1.750   0.2089   0.00941   0.00204  -0.0787   0.6364   0.1372
  -1.500   0.2368   0.00938   0.00200  -0.0787   0.6270   0.1501
  -1.000   0.2927   0.00934   0.00192  -0.0787   0.6090   0.1687
  -0.750   0.3203   0.00933   0.00189  -0.0787   0.5981   0.1801
  -0.250   0.3754   0.00921   0.00186  -0.0786   0.5770   0.2348
   0.000   0.4026   0.00908   0.00187  -0.0786   0.5672   0.2975
   0.250   0.4293   0.00890   0.00189  -0.0785   0.5553   0.3781
   0.500   0.4556   0.00858   0.00192  -0.0784   0.5442   0.5033
   0.750   0.4809   0.00823   0.00198  -0.0780   0.5355   0.6437
   1.000   0.5049   0.00793   0.00205  -0.0771   0.5276   0.7697
   1.250   0.5278   0.00777   0.00214  -0.0757   0.5206   0.8625
   1.500   0.5565   0.00773   0.00222  -0.0755   0.5134   0.9398
   1.750   0.5941   0.00782   0.00226  -0.0775   0.5056   0.9759
   2.000   0.6300   0.00791   0.00231  -0.0793   0.4959   0.9935
   2.250   0.6616   0.00802   0.00236  -0.0802   0.4860   1.0000
   2.500   0.6875   0.00814   0.00243  -0.0798   0.4761   1.0000
   2.750   0.7139   0.00825   0.00250  -0.0796   0.4657   1.0000
   3.000   0.7401   0.00838   0.00258  -0.0792   0.4544   1.0000
   3.250   0.7661   0.00853   0.00267  -0.0789   0.4410   1.0000
   3.500   0.7919   0.00871   0.00278  -0.0786   0.4238   1.0000
   3.750   0.8169   0.00895   0.00291  -0.0781   0.4011   1.0000
   4.000   0.8414   0.00925   0.00308  -0.0776   0.3742   1.0000
   4.250   0.8656   0.00958   0.00327  -0.0770   0.3491   1.0000
   4.500   0.8900   0.00991   0.00349  -0.0765   0.3276   1.0000
   4.750   0.9145   0.01023   0.00373  -0.0760   0.3092   1.0000
   5.250   0.9638   0.01084   0.00420  -0.0751   0.2784   1.0000
   5.500   0.9886   0.01113   0.00444  -0.0747   0.2653   1.0000
   5.750   1.0133   0.01142   0.00469  -0.0743   0.2536   1.0000
   6.000   1.0377   0.01173   0.00496  -0.0738   0.2426   1.0000
   6.500   1.0865   0.01233   0.00552  -0.0729   0.2240   1.0000
   6.750   1.1103   0.01266   0.00582  -0.0724   0.2164   1.0000
   7.000   1.1345   0.01295   0.00612  -0.0719   0.2087   1.0000
   7.250   1.1577   0.01331   0.00644  -0.0713   0.2011   1.0000
   7.500   1.1813   0.01362   0.00676  -0.0707   0.1933   1.0000
   7.750   1.2039   0.01400   0.00711  -0.0700   0.1852   1.0000
   8.000   1.2266   0.01435   0.00746  -0.0693   0.1774   1.0000
   8.250   1.2488   0.01472   0.00783  -0.0686   0.1712   1.0000
   8.500   1.2712   0.01507   0.00819  -0.0679   0.1645   1.0000
   8.750   1.2922   0.01549   0.00860  -0.0670   0.1570   1.0000
   9.000   1.3134   0.01588   0.00901  -0.0661   0.1489   1.0000
   9.250   1.3333   0.01633   0.00945  -0.0650   0.1394   1.0000
   9.500   1.3516   0.01685   0.00993  -0.0638   0.1271   1.0000
   9.750   1.3660   0.01749   0.01049  -0.0618   0.1095   1.0000
  10.000   1.3656   0.01900   0.01168  -0.0579   0.0654   1.0000
  10.250   1.3725   0.02016   0.01278  -0.0552   0.0501   1.0000
  10.500   1.3828   0.02115   0.01376  -0.0531   0.0408   1.0000
  10.750   1.3930   0.02218   0.01478  -0.0512   0.0323   1.0000
  11.000   1.4025   0.02330   0.01589  -0.0493   0.0249   1.0000
  11.250   1.4119   0.02447   0.01707  -0.0475   0.0202   1.0000
  11.500   1.4212   0.02569   0.01832  -0.0459   0.0175   1.0000
  11.750   1.4313   0.02688   0.01958  -0.0445   0.0159   1.0000
  12.000   1.4400   0.02824   0.02100  -0.0431   0.0146   1.0000
  12.250   1.4473   0.02974   0.02257  -0.0417   0.0136   1.0000
  12.500   1.4562   0.03117   0.02408  -0.0405   0.0130   1.0000
  12.750   1.4637   0.03276   0.02576  -0.0394   0.0124   1.0000
  13.000   1.4696   0.03453   0.02761  -0.0384   0.0118   1.0000
  13.250   1.4740   0.03651   0.02968  -0.0374   0.0113   1.0000
  13.500   1.4762   0.03877   0.03203  -0.0365   0.0109   1.0000
  13.750   1.4770   0.04125   0.03461  -0.0357   0.0105   1.0000
  14.000   1.4799   0.04360   0.03706  -0.0352   0.0102   1.0000
  14.250   1.4817   0.04614   0.03971  -0.0349   0.0099   1.0000
  14.500   1.4819   0.04892   0.04260  -0.0346   0.0096   1.0000
  14.750   1.4810   0.05194   0.04572  -0.0345   0.0093   1.0000
  15.000   1.4794   0.05515   0.04904  -0.0346   0.0090   1.0000
  15.250   1.4759   0.05866   0.05266  -0.0349   0.0088   1.0000
  15.500   1.4708   0.06249   0.05659  -0.0353   0.0086   1.0000
  15.750   1.4640   0.06663   0.06084  -0.0360   0.0084   1.0000
  16.000   1.4553   0.07114   0.06547  -0.0368   0.0083   1.0000
  16.250   1.4447   0.07600   0.07044  -0.0378   0.0082   1.0000
  16.500   1.4318   0.08133   0.07590  -0.0391   0.0081   1.0000
  16.750   1.4201   0.08664   0.08134  -0.0406   0.0080   1.0000
  17.000   1.4096   0.09183   0.08665  -0.0420   0.0079   1.0000
  17.250   1.3983   0.09727   0.09222  -0.0437   0.0078   1.0000
  17.500   1.3866   0.10290   0.09797  -0.0456   0.0077   1.0000
  17.750   1.3750   0.10859   0.10378  -0.0476   0.0077   1.0000
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