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GOE 57 AIRFOIL (goe57-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 57 AIRFOIL (goe57-il)
Reynolds number: 1,000,000
Max Cl/Cd: 102.2 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe57-il-1000000-n5.txt
Download as CSV file: xf-goe57-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 57 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3531   0.10281   0.10121  -0.0242   1.0000   0.0060
  -9.250  -0.3574   0.09767   0.09608  -0.0258   1.0000   0.0067
  -9.000  -0.3591   0.09391   0.09235  -0.0267   1.0000   0.0070
  -8.750  -0.3559   0.09173   0.09019  -0.0267   1.0000   0.0072
  -8.250  -0.3212   0.08516   0.08362  -0.0350   0.9873   0.0078
  -8.000  -0.3045   0.08104   0.07949  -0.0403   0.9725   0.0085
  -7.750  -0.2851   0.07372   0.07213  -0.0508   0.9482   0.0098
  -7.500  -0.2638   0.07091   0.06924  -0.0551   0.9240   0.0101
  -7.250  -0.2449   0.06833   0.06657  -0.0585   0.9056   0.0104
  -7.000  -0.2251   0.06534   0.06349  -0.0625   0.8918   0.0110
  -6.750  -0.2005   0.05644   0.05447  -0.0750   0.8795   0.0135
  -6.500  -0.1764   0.05460   0.05257  -0.0778   0.8711   0.0138
  -6.250  -0.1517   0.05257   0.05046  -0.0807   0.8628   0.0141
  -6.000  -0.1257   0.05008   0.04790  -0.0842   0.8530   0.0147
  -5.750  -0.0862   0.04086   0.03844  -0.0964   0.8452   0.0181
  -5.500  -0.0559   0.03687   0.03429  -0.1010   0.8352   0.0188
  -5.250  -0.0294   0.03567   0.03301  -0.1023   0.8251   0.0191
  -5.000  -0.0023   0.03417   0.03140  -0.1037   0.8140   0.0195
  -4.750   0.0251   0.03239   0.02948  -0.1053   0.7979   0.0200
  -4.500   0.0530   0.03036   0.02727  -0.1069   0.7772   0.0207
  -4.250   0.0819   0.02805   0.02476  -0.1085   0.7569   0.0218
  -4.000   0.1127   0.02447   0.02087  -0.1106   0.7376   0.0228
  -3.750   0.1455   0.01702   0.01276  -0.1135   0.7218   0.0237
  -3.500   0.1730   0.01263   0.00767  -0.1144   0.6995   0.0246
  -3.250   0.1995   0.01199   0.00675  -0.1142   0.6682   0.0249
  -3.000   0.2262   0.01164   0.00617  -0.1140   0.6409   0.0251
  -2.750   0.2533   0.01140   0.00577  -0.1139   0.6192   0.0253
  -2.500   0.2803   0.01004   0.00404  -0.1140   0.5996   0.0265
  -2.250   0.3073   0.00979   0.00364  -0.1138   0.5751   0.0271
  -2.000   0.3342   0.00965   0.00334  -0.1136   0.5472   0.0275
  -1.750   0.3611   0.00954   0.00308  -0.1134   0.5180   0.0278
  -1.500   0.3874   0.00952   0.00285  -0.1131   0.4757   0.0281
  -1.250   0.4134   0.00956   0.00266  -0.1127   0.4294   0.0283
  -1.000   0.4397   0.00959   0.00248  -0.1125   0.3907   0.0285
  -0.750   0.4663   0.00959   0.00233  -0.1122   0.3606   0.0287
  -0.500   0.4931   0.00958   0.00219  -0.1120   0.3347   0.0289
  -0.250   0.5199   0.00963   0.00211  -0.1118   0.3089   0.0293
   0.000   0.5463   0.00975   0.00208  -0.1115   0.2765   0.0298
   0.250   0.5727   0.00986   0.00203  -0.1113   0.2439   0.0301
   0.500   0.5978   0.01017   0.00207  -0.1108   0.1871   0.0304
   0.750   0.6249   0.01021   0.00204  -0.1106   0.1770   0.0308
   1.000   0.6522   0.01024   0.00203  -0.1105   0.1714   0.0315
   1.250   0.6795   0.01027   0.00204  -0.1104   0.1684   0.0326
   1.500   0.7068   0.01032   0.00208  -0.1102   0.1658   0.0339
   1.750   0.7340   0.01038   0.00212  -0.1100   0.1633   0.0363
   2.000   0.7613   0.01043   0.00219  -0.1099   0.1610   0.0414
   2.250   0.7884   0.01051   0.00227  -0.1097   0.1590   0.0454
   2.500   0.8156   0.01057   0.00236  -0.1096   0.1582   0.0516
   2.750   0.8428   0.01063   0.00245  -0.1094   0.1574   0.0592
   3.250   0.8966   0.01079   0.00269  -0.1091   0.1505   0.1038
   3.500   0.9236   0.01076   0.00289  -0.1091   0.1474   0.2358
   3.750   0.9462   0.00957   0.00319  -0.1084   0.1440   1.0000
   4.000   0.9733   0.00968   0.00329  -0.1083   0.1423   1.0000
   4.250   1.0001   0.00982   0.00341  -0.1081   0.1389   1.0000
   4.500   1.0261   0.01004   0.00356  -0.1078   0.1300   1.0000
   4.750   1.0484   0.01075   0.00396  -0.1070   0.0731   1.0000
   5.000   1.0696   0.01162   0.00457  -0.1059   0.0180   1.0000
   5.250   1.0951   0.01190   0.00486  -0.1055   0.0136   1.0000
   5.500   1.1204   0.01220   0.00517  -0.1051   0.0112   1.0000
   5.750   1.1458   0.01247   0.00547  -0.1046   0.0103   1.0000
   6.000   1.1710   0.01276   0.00577  -0.1042   0.0094   1.0000
   6.250   1.1959   0.01308   0.00611  -0.1038   0.0084   1.0000
   6.500   1.2201   0.01347   0.00652  -0.1032   0.0075   1.0000
   6.750   1.2441   0.01388   0.00696  -0.1026   0.0070   1.0000
   7.000   1.2683   0.01425   0.00736  -0.1020   0.0066   1.0000
   7.250   1.2921   0.01465   0.00780  -0.1014   0.0062   1.0000
   7.500   1.3157   0.01505   0.00822  -0.1007   0.0057   1.0000
   7.750   1.3390   0.01546   0.00865  -0.1001   0.0053   1.0000
   8.000   1.3604   0.01611   0.00934  -0.0991   0.0048   1.0000
   8.250   1.3828   0.01659   0.00987  -0.0983   0.0047   1.0000
   8.500   1.4046   0.01713   0.01046  -0.0974   0.0045   1.0000
   8.750   1.4258   0.01771   0.01111  -0.0964   0.0042   1.0000
   9.000   1.4462   0.01833   0.01179  -0.0954   0.0040   1.0000
   9.250   1.4662   0.01896   0.01248  -0.0942   0.0039   1.0000
   9.500   1.4855   0.01961   0.01318  -0.0930   0.0037   1.0000
   9.750   1.5043   0.02026   0.01389  -0.0918   0.0036   1.0000
  10.000   1.5222   0.02096   0.01464  -0.0904   0.0034   1.0000
  10.250   1.5379   0.02179   0.01553  -0.0887   0.0033   1.0000
  10.500   1.5467   0.02311   0.01697  -0.0861   0.0031   1.0000
  10.750   1.5591   0.02390   0.01784  -0.0838   0.0030   1.0000
  11.000   1.5691   0.02476   0.01879  -0.0813   0.0030   1.0000
  11.250   1.5774   0.02576   0.01988  -0.0786   0.0029   1.0000
  11.500   1.5833   0.02695   0.02117  -0.0758   0.0028   1.0000
  11.750   1.5874   0.02833   0.02265  -0.0730   0.0027   1.0000
  12.000   1.5903   0.02989   0.02433  -0.0705   0.0027   1.0000
  12.250   1.5919   0.03167   0.02622  -0.0681   0.0026   1.0000
  12.500   1.5929   0.03364   0.02830  -0.0660   0.0025   1.0000
  12.750   1.5926   0.03584   0.03061  -0.0641   0.0025   1.0000
  13.000   1.5918   0.03825   0.03313  -0.0626   0.0024   1.0000
  13.250   1.5895   0.04093   0.03593  -0.0613   0.0024   1.0000
  13.500   1.5873   0.04377   0.03891  -0.0604   0.0024   1.0000
  13.750   1.5820   0.04713   0.04239  -0.0597   0.0023   1.0000
  14.000   1.5772   0.05062   0.04601  -0.0595   0.0023   1.0000
  14.250   1.5715   0.05444   0.04994  -0.0596   0.0023   1.0000
  14.500   1.5640   0.05866   0.05429  -0.0601   0.0022   1.0000
  14.750   1.5568   0.06304   0.05879  -0.0609   0.0022   1.0000
  15.000   1.5470   0.06799   0.06386  -0.0620   0.0022   1.0000
  15.250   1.5355   0.07332   0.06933  -0.0634   0.0022   1.0000
  15.500   1.5243   0.07883   0.07496  -0.0651   0.0022   1.0000
  15.750   1.5113   0.08477   0.08103  -0.0670   0.0022   1.0000
  16.000   1.5008   0.09046   0.08683  -0.0691   0.0021   1.0000
  16.250   1.4871   0.09671   0.09320  -0.0713   0.0021   1.0000
  16.500   1.4740   0.10298   0.09959  -0.0737   0.0021   1.0000
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