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GOE 359 AIRFOIL (goe359-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 359 AIRFOIL (goe359-il)
Reynolds number: 500,000
Max Cl/Cd: 103.94 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe359-il-500000-n5.txt
Download as CSV file: xf-goe359-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 359 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  -0.1375   0.08688   0.08479  -0.0458   0.9345   0.0077
  -8.750  -0.2647   0.10309   0.10095  -0.0283   1.0000   0.0085
  -8.250  -0.2373   0.09598   0.09385  -0.0343   0.9845   0.0074
  -8.000  -0.2190   0.09151   0.08936  -0.0394   0.9483   0.0071
  -7.500  -0.1818   0.08273   0.08034  -0.0499   0.8766   0.0068
  -7.250  -0.1738   0.07965   0.07717  -0.0520   0.8539   0.0069
  -7.000  -0.1616   0.07621   0.07366  -0.0554   0.8369   0.0070
  -6.750  -0.1470   0.07259   0.06996  -0.0595   0.8220   0.0071
  -6.500  -0.1300   0.06875   0.06606  -0.0641   0.8085   0.0075
  -6.250  -0.1095   0.06386   0.06111  -0.0705   0.7962   0.0082
  -6.000  -0.0859   0.05859   0.05575  -0.0775   0.7850   0.0085
  -5.750  -0.0587   0.05294   0.05000  -0.0850   0.7744   0.0088
  -5.250  -0.0041   0.04645   0.04329  -0.0939   0.7513   0.0096
  -5.000   0.0266   0.04242   0.03911  -0.0989   0.7397   0.0104
  -4.750   0.0683   0.03309   0.02940  -0.1083   0.7303   0.0127
  -4.500   0.0954   0.03162   0.02779  -0.1096   0.7180   0.0133
  -4.250   0.1348   0.01937   0.01455  -0.1155   0.7102   0.0183
  -4.000   0.1611   0.01942   0.01454  -0.1156   0.6982   0.0189
  -3.750   0.1875   0.01935   0.01436  -0.1155   0.6865   0.0196
  -3.250   0.2416   0.01783   0.01243  -0.1157   0.6631   0.0228
  -3.000   0.2697   0.01633   0.01055  -0.1158   0.6521   0.0248
  -2.750   0.2973   0.01592   0.00990  -0.1156   0.6412   0.0261
  -2.500   0.3247   0.01558   0.00936  -0.1155   0.6307   0.0267
  -2.250   0.3522   0.01458   0.00807  -0.1155   0.6202   0.0272
  -2.000   0.3793   0.01316   0.00637  -0.1155   0.6092   0.0283
  -1.750   0.4064   0.01258   0.00561  -0.1154   0.5974   0.0289
  -1.500   0.4336   0.01208   0.00495  -0.1152   0.5852   0.0292
  -1.250   0.4609   0.01168   0.00444  -0.1151   0.5736   0.0298
  -1.000   0.4881   0.01137   0.00402  -0.1149   0.5621   0.0306
  -0.750   0.5153   0.01113   0.00369  -0.1148   0.5515   0.0316
  -0.250   0.5699   0.01074   0.00316  -0.1144   0.5319   0.0333
   0.000   0.5970   0.01060   0.00295  -0.1143   0.5222   0.0339
   0.250   0.6240   0.01049   0.00277  -0.1141   0.5108   0.0343
   0.500   0.6510   0.01041   0.00264  -0.1139   0.4992   0.0350
   0.750   0.6782   0.01036   0.00255  -0.1138   0.4897   0.0360
   1.000   0.7051   0.01031   0.00246  -0.1136   0.4801   0.0362
   1.500   0.7585   0.01031   0.00232  -0.1132   0.4534   0.0362
   1.750   0.7853   0.01034   0.00229  -0.1130   0.4403   0.0363
   2.000   0.8122   0.01037   0.00229  -0.1128   0.4307   0.0366
   2.250   0.8390   0.01044   0.00230  -0.1126   0.4214   0.0371
   2.500   0.8658   0.01051   0.00233  -0.1125   0.4113   0.0379
   2.750   0.8926   0.01059   0.00238  -0.1123   0.4018   0.0404
   3.000   0.9192   0.01067   0.00244  -0.1121   0.3923   0.0533
   3.250   0.9459   0.01053   0.00265  -0.1121   0.3809   0.2447
   3.750   0.9947   0.00957   0.00304  -0.1112   0.3508   1.0000
   4.000   1.0200   0.00985   0.00320  -0.1108   0.3267   1.0000
   4.250   1.0414   0.01054   0.00355  -0.1099   0.2668   1.0000
   4.500   1.0633   0.01119   0.00394  -0.1091   0.2275   1.0000
   4.750   1.0862   0.01173   0.00430  -0.1084   0.1993   1.0000
   5.000   1.1081   0.01236   0.00469  -0.1076   0.1586   1.0000
   5.250   1.1229   0.01375   0.00557  -0.1058   0.0679   1.0000
   5.500   1.1451   0.01432   0.00605  -0.1050   0.0504   1.0000
   5.750   1.1685   0.01474   0.00644  -0.1044   0.0397   1.0000
   6.000   1.1897   0.01537   0.00695  -0.1035   0.0164   1.0000
   6.250   1.2133   0.01575   0.00740  -0.1028   0.0128   1.0000
   6.500   1.2365   0.01614   0.00786  -0.1022   0.0115   1.0000
   6.750   1.2590   0.01660   0.00841  -0.1014   0.0102   1.0000
   7.000   1.2793   0.01725   0.00917  -0.1002   0.0088   1.0000
   7.250   1.3012   0.01772   0.00969  -0.0994   0.0081   1.0000
   7.500   1.3219   0.01827   0.01034  -0.0984   0.0075   1.0000
   7.750   1.3416   0.01889   0.01104  -0.0972   0.0069   1.0000
   8.000   1.3599   0.01960   0.01182  -0.0958   0.0065   1.0000
   8.250   1.3744   0.02058   0.01290  -0.0940   0.0060   1.0000
   8.500   1.3924   0.02121   0.01359  -0.0926   0.0055   1.0000
   8.750   1.4066   0.02207   0.01454  -0.0907   0.0052   1.0000
   9.000   1.4171   0.02301   0.01558  -0.0882   0.0049   1.0000
   9.250   1.4257   0.02404   0.01669  -0.0855   0.0047   1.0000
   9.500   1.4330   0.02517   0.01791  -0.0829   0.0045   1.0000
   9.750   1.4387   0.02647   0.01930  -0.0803   0.0044   1.0000
  10.000   1.4422   0.02801   0.02093  -0.0778   0.0042   1.0000
  10.250   1.4421   0.02999   0.02301  -0.0754   0.0041   1.0000
  10.500   1.4371   0.03259   0.02572  -0.0731   0.0040   1.0000
  10.750   1.4377   0.03490   0.02814  -0.0716   0.0040   1.0000
  11.000   1.4376   0.03741   0.03077  -0.0703   0.0039   1.0000
  11.250   1.4374   0.04005   0.03351  -0.0692   0.0038   1.0000
  11.500   1.4373   0.04275   0.03633  -0.0683   0.0037   1.0000
  11.750   1.4372   0.04555   0.03923  -0.0675   0.0035   1.0000
  12.000   1.4370   0.04841   0.04220  -0.0669   0.0033   1.0000
  12.250   1.4361   0.05139   0.04531  -0.0664   0.0032   1.0000
  12.500   1.4347   0.05448   0.04849  -0.0660   0.0031   1.0000
  12.750   1.4326   0.05764   0.05175  -0.0655   0.0030   1.0000
  13.000   1.4309   0.06082   0.05502  -0.0652   0.0030   1.0000
  13.250   1.4292   0.06404   0.05834  -0.0649   0.0029   1.0000
  13.500   1.4274   0.06734   0.06174  -0.0648   0.0028   1.0000
  13.750   1.4256   0.07071   0.06521  -0.0648   0.0028   1.0000
  14.000   1.4236   0.07421   0.06880  -0.0650   0.0027   1.0000
  14.250   1.4214   0.07775   0.07244  -0.0651   0.0027   1.0000
  14.500   1.4185   0.08142   0.07621  -0.0654   0.0027   1.0000
  14.750   1.4155   0.08510   0.07999  -0.0656   0.0026   1.0000
  15.000   1.4115   0.08886   0.08385  -0.0656   0.0026   1.0000
  15.250   1.4083   0.09267   0.08779  -0.0657   0.0025   1.0000
  15.500   1.4047   0.09664   0.09191  -0.0660   0.0025   1.0000
  15.750   1.4002   0.10084   0.09626  -0.0665   0.0025   1.0000
  16.000   1.3945   0.10539   0.10097  -0.0674   0.0024   1.0000
  16.250   1.3876   0.11030   0.10604  -0.0686   0.0024   1.0000
  16.500   1.3795   0.11553   0.11144  -0.0704   0.0024   1.0000
  16.750   1.3705   0.12107   0.11714  -0.0725   0.0024   1.0000
  17.000   1.3613   0.12684   0.12306  -0.0751   0.0024   1.0000
  17.250   1.3514   0.13296   0.12935  -0.0780   0.0023   1.0000
  17.500   1.3417   0.13922   0.13576  -0.0813   0.0023   1.0000
  17.750   1.3312   0.14588   0.14257  -0.0850   0.0023   1.0000
  18.000   1.3213   0.15257   0.14941  -0.0889   0.0024   1.0000
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