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GOE 457 AIRFOIL (goe457-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 457 AIRFOIL (goe457-il)
Reynolds number: 500,000
Max Cl/Cd: 93.48 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe457-il-500000-n5.txt
Download as CSV file: xf-goe457-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 457 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3680   0.09678   0.09454  -0.0236   1.0000   0.0078
  -8.750  -0.3714   0.09372   0.09151  -0.0234   1.0000   0.0078
  -8.500  -0.3770   0.09090   0.08873  -0.0227   1.0000   0.0079
  -7.500  -0.3658   0.01978   0.01584  -0.0942   0.9676   0.0116
  -7.250  -0.3330   0.01990   0.01601  -0.0953   0.9662   0.0122
  -7.000  -0.3014   0.02026   0.01642  -0.0959   0.9641   0.0127
  -6.750  -0.2738   0.02043   0.01659  -0.0958   0.9597   0.0134
  -6.500  -0.2479   0.01641   0.01182  -0.0970   0.9559   0.0154
  -6.250  -0.2141   0.01600   0.01134  -0.0983   0.9536   0.0162
  -6.000  -0.1846   0.01602   0.01137  -0.0986   0.9493   0.0169
  -5.750  -0.1550   0.01589   0.01119  -0.0990   0.9443   0.0179
  -5.500  -0.1232   0.01509   0.01018  -0.0999   0.9408   0.0197
  -5.250  -0.0915   0.01448   0.00936  -0.1006   0.9369   0.0209
  -5.000  -0.0643   0.01354   0.00825  -0.1007   0.9303   0.0220
  -4.750  -0.0316   0.01319   0.00786  -0.1017   0.9251   0.0231
  -4.500  -0.0025   0.01281   0.00741  -0.1019   0.9185   0.0242
  -4.250   0.0273   0.01235   0.00683  -0.1023   0.9121   0.0255
  -4.000   0.0566   0.01192   0.00628  -0.1024   0.9054   0.0267
  -3.750   0.0849   0.01145   0.00569  -0.1024   0.8974   0.0276
  -3.500   0.1129   0.01107   0.00521  -0.1022   0.8883   0.0283
  -3.250   0.1414   0.01084   0.00489  -0.1021   0.8782   0.0290
  -3.000   0.1679   0.01035   0.00428  -0.1017   0.8657   0.0295
  -2.750   0.1940   0.00978   0.00360  -0.1011   0.8499   0.0302
  -2.500   0.2198   0.00940   0.00312  -0.1005   0.8254   0.0308
  -2.250   0.2447   0.00920   0.00271  -0.0995   0.7772   0.0314
  -2.000   0.2665   0.00924   0.00243  -0.0979   0.7169   0.0321
  -1.750   0.2884   0.00931   0.00225  -0.0965   0.6657   0.0330
  -1.500   0.3107   0.00941   0.00210  -0.0952   0.6152   0.0337
  -1.250   0.3337   0.00949   0.00197  -0.0940   0.5744   0.0344
  -1.000   0.3581   0.00954   0.00186  -0.0932   0.5477   0.0353
  -0.750   0.3832   0.00956   0.00177  -0.0925   0.5282   0.0365
  -0.500   0.4089   0.00958   0.00170  -0.0919   0.5134   0.0377
  -0.250   0.4348   0.00960   0.00164  -0.0914   0.5005   0.0392
   0.000   0.4609   0.00962   0.00161  -0.0909   0.4894   0.0429
   0.500   0.5131   0.00959   0.00163  -0.0900   0.4686   0.0794
   0.750   0.5392   0.00960   0.00165  -0.0896   0.4597   0.0965
   1.000   0.5643   0.00938   0.00172  -0.0891   0.4501   0.2140
   1.250   0.5900   0.00930   0.00179  -0.0886   0.4407   0.2868
   1.500   0.6149   0.00916   0.00187  -0.0881   0.4311   0.3865
   2.000   0.6850   0.00808   0.00212  -0.0914   0.4102   1.0000
   2.250   0.7103   0.00823   0.00218  -0.0908   0.3982   1.0000
   2.500   0.7355   0.00839   0.00227  -0.0902   0.3856   1.0000
   2.750   0.7608   0.00855   0.00235  -0.0896   0.3734   1.0000
   3.000   0.7859   0.00872   0.00245  -0.0890   0.3594   1.0000
   3.250   0.8106   0.00893   0.00256  -0.0883   0.3419   1.0000
   3.500   0.8353   0.00915   0.00269  -0.0876   0.3226   1.0000
   3.750   0.8603   0.00934   0.00283  -0.0870   0.3099   1.0000
   4.000   0.8853   0.00955   0.00297  -0.0864   0.2988   1.0000
   4.250   0.9101   0.00976   0.00314  -0.0858   0.2853   1.0000
   4.750   0.9591   0.01026   0.00351  -0.0845   0.2550   1.0000
   5.000   0.9834   0.01053   0.00372  -0.0838   0.2390   1.0000
   5.250   1.0076   0.01081   0.00395  -0.0832   0.2233   1.0000
   5.500   1.0316   0.01111   0.00419  -0.0825   0.2070   1.0000
   5.750   1.0543   0.01154   0.00450  -0.0816   0.1792   1.0000
   6.250   1.0954   0.01285   0.00539  -0.0793   0.1070   1.0000
   6.500   1.1180   0.01328   0.00577  -0.0784   0.0947   1.0000
   6.750   1.1401   0.01374   0.00618  -0.0775   0.0815   1.0000
   7.000   1.1624   0.01416   0.00656  -0.0766   0.0719   1.0000
   7.250   1.1847   0.01457   0.00694  -0.0757   0.0637   1.0000
   7.500   1.2068   0.01500   0.00733  -0.0748   0.0554   1.0000
   7.750   1.2279   0.01549   0.00778  -0.0737   0.0456   1.0000
   8.000   1.2435   0.01649   0.00859  -0.0719   0.0177   1.0000
   8.250   1.2635   0.01706   0.00921  -0.0706   0.0132   1.0000
   8.500   1.2834   0.01760   0.00983  -0.0693   0.0116   1.0000
   8.750   1.3017   0.01826   0.01058  -0.0677   0.0102   1.0000
   9.000   1.3198   0.01890   0.01132  -0.0662   0.0094   1.0000
   9.250   1.3384   0.01946   0.01197  -0.0647   0.0088   1.0000
   9.500   1.3559   0.02008   0.01269  -0.0631   0.0082   1.0000
   9.750   1.3724   0.02073   0.01342  -0.0614   0.0076   1.0000
  10.000   1.3859   0.02150   0.01427  -0.0592   0.0070   1.0000
  10.250   1.3947   0.02248   0.01536  -0.0563   0.0066   1.0000
  10.500   1.4070   0.02320   0.01616  -0.0539   0.0064   1.0000
  10.750   1.4167   0.02408   0.01714  -0.0513   0.0062   1.0000
  11.000   1.4260   0.02499   0.01815  -0.0487   0.0059   1.0000
  11.250   1.4333   0.02603   0.01931  -0.0460   0.0057   1.0000
  11.500   1.4392   0.02719   0.02058  -0.0434   0.0055   1.0000
  11.750   1.4439   0.02847   0.02196  -0.0408   0.0054   1.0000
  12.000   1.4486   0.02980   0.02339  -0.0384   0.0051   1.0000
  12.250   1.4507   0.03139   0.02508  -0.0361   0.0050   1.0000
  12.500   1.4525   0.03309   0.02688  -0.0340   0.0049   1.0000
  12.750   1.4501   0.03526   0.02916  -0.0320   0.0047   1.0000
  13.000   1.4451   0.03785   0.03187  -0.0304   0.0046   1.0000
  13.250   1.4374   0.04100   0.03516  -0.0293   0.0045   1.0000
  13.500   1.4356   0.04381   0.03810  -0.0289   0.0044   1.0000
  13.750   1.4288   0.04751   0.04194  -0.0291   0.0044   1.0000
  14.000   1.4245   0.05119   0.04576  -0.0297   0.0043   1.0000
  14.250   1.4190   0.05530   0.05002  -0.0309   0.0042   1.0000
  14.500   1.4100   0.06017   0.05503  -0.0324   0.0041   1.0000
  14.750   1.3993   0.06538   0.06039  -0.0343   0.0041   1.0000
  15.000   1.3886   0.07070   0.06586  -0.0363   0.0040   1.0000
  15.250   1.3773   0.07623   0.07152  -0.0385   0.0040   1.0000
  15.500   1.3646   0.08204   0.07746  -0.0408   0.0040   1.0000
  15.750   1.3536   0.08777   0.08331  -0.0432   0.0039   1.0000
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