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GOE 604 AIRFOIL (goe604-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 604 AIRFOIL (goe604-il)
Reynolds number: 100,000
Max Cl/Cd: 29.83 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe604-il-100000.txt
Download as CSV file: xf-goe604-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 604 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.1653   0.10284   0.09870  -0.0574   0.9691   0.1644
  -9.500  -0.1489   0.09678   0.09265  -0.0647   0.9571   0.1676
  -9.250  -0.2530   0.06719   0.06284  -0.0961   0.9375   0.1098
  -9.000  -0.2324   0.06186   0.05742  -0.1006   0.9221   0.1083
  -8.750  -0.2351   0.05502   0.05037  -0.1052   0.9037   0.1058
  -8.500  -0.3177   0.04283   0.03690  -0.1037   0.8770   0.0990
  -8.250  -0.2964   0.03972   0.03351  -0.1043   0.8649   0.1000
  -8.000  -0.2745   0.03832   0.03202  -0.1037   0.8491   0.1025
  -7.750  -0.2627   0.03617   0.02952  -0.1021   0.8338   0.1045
  -7.500  -0.2503   0.03391   0.02681  -0.1003   0.8200   0.1065
  -7.250  -0.2328   0.03165   0.02397  -0.0988   0.8092   0.1086
  -7.000  -0.2140   0.03026   0.02240  -0.0974   0.7959   0.1114
  -6.750  -0.1911   0.02951   0.02158  -0.0965   0.7838   0.1154
  -6.500  -0.1669   0.02824   0.01993  -0.0955   0.7742   0.1200
  -6.250  -0.1468   0.02722   0.01877  -0.0941   0.7621   0.1240
  -6.000  -0.1211   0.02661   0.01805  -0.0934   0.7527   0.1306
  -5.750  -0.0992   0.02582   0.01710  -0.0922   0.7418   0.1378
  -5.500  -0.0747   0.02527   0.01644  -0.0913   0.7325   0.1470
  -5.250  -0.0515   0.02466   0.01585  -0.0902   0.7227   0.1583
  -5.000  -0.0281   0.02411   0.01525  -0.0892   0.7139   0.1740
  -4.750  -0.0062   0.02365   0.01477  -0.0879   0.7045   0.1953
  -4.500   0.0168   0.02328   0.01439  -0.0868   0.6964   0.2204
  -4.250   0.0380   0.02317   0.01433  -0.0854   0.6870   0.2427
  -4.000   0.0638   0.02306   0.01412  -0.0847   0.6800   0.2644
  -3.750   0.0839   0.02306   0.01416  -0.0833   0.6704   0.2815
  -3.500   0.1109   0.02290   0.01389  -0.0827   0.6635   0.2996
  -3.250   0.1315   0.02292   0.01393  -0.0814   0.6547   0.3157
  -3.000   0.1568   0.02279   0.01376  -0.0806   0.6472   0.3343
  -2.750   0.1803   0.02276   0.01374  -0.0797   0.6398   0.3544
  -2.500   0.2027   0.02269   0.01372  -0.0786   0.6316   0.3745
  -2.250   0.2313   0.02241   0.01340  -0.0783   0.6257   0.3964
  -2.000   0.2507   0.02239   0.01352  -0.0769   0.6170   0.4199
  -1.750   0.2761   0.02209   0.01333  -0.0761   0.6100   0.4526
  -1.500   0.2999   0.02187   0.01329  -0.0751   0.6035   0.4962
  -1.250   0.3189   0.02171   0.01347  -0.0733   0.5953   0.5560
  -1.000   0.3461   0.02123   0.01345  -0.0722   0.5896   0.6681
  -0.750   0.3945   0.02132   0.01408  -0.0745   0.5811   0.8471
  -0.500   0.4738   0.02169   0.01423  -0.0827   0.5724   0.9355
  -0.250   0.5526   0.02215   0.01445  -0.0920   0.5630   0.9750
   0.000   0.6306   0.02219   0.01420  -0.1017   0.5542   1.0000
   0.250   0.6482   0.02242   0.01424  -0.1003   0.5495   1.0000
   0.500   0.6558   0.02298   0.01484  -0.0975   0.5423   1.0000
   0.750   0.6730   0.02328   0.01501  -0.0959   0.5369   1.0000
   1.000   0.6959   0.02349   0.01502  -0.0950   0.5328   1.0000
   1.250   0.7028   0.02426   0.01586  -0.0920   0.5261   1.0000
   1.500   0.7187   0.02470   0.01623  -0.0901   0.5205   1.0000
   1.750   0.7422   0.02491   0.01627  -0.0893   0.5162   1.0000
   2.000   0.7567   0.02556   0.01688  -0.0872   0.5112   1.0000
   2.250   0.7653   0.02640   0.01777  -0.0844   0.5053   1.0000
   2.500   0.7844   0.02686   0.01816  -0.0830   0.5010   1.0000
   2.750   0.8100   0.02715   0.01830  -0.0825   0.4977   1.0000
   3.000   0.8199   0.02816   0.01934  -0.0800   0.4933   1.0000
   3.250   0.8218   0.02946   0.02074  -0.0765   0.4880   1.0000
   3.500   0.8399   0.03006   0.02129  -0.0750   0.4840   1.0000
   3.750   0.8657   0.03034   0.02147  -0.0745   0.4808   1.0000
   4.000   0.8925   0.03075   0.02176  -0.0743   0.4778   1.0000
   4.250   0.8636   0.03350   0.02480  -0.0671   0.4715   1.0000
   4.500   0.8668   0.03494   0.02628  -0.0641   0.4674   1.0000
   4.750   0.8896   0.03548   0.02676  -0.0634   0.4646   1.0000
   5.000   0.9208   0.03570   0.02689  -0.0637   0.4624   1.0000
   5.250   0.4271   0.07967   0.07185  -0.0439   0.4695   1.0000
   5.500   0.4562   0.08034   0.07245  -0.0435   0.4643   1.0000
   5.750   0.4750   0.08224   0.07431  -0.0434   0.4628   1.0000
   6.000   0.4802   0.08516   0.07723  -0.0434   0.4625   1.0000
   6.250   0.4874   0.08804   0.08009  -0.0434   0.4621   1.0000
   6.500   0.4968   0.09090   0.08294  -0.0435   0.4617   1.0000
   6.750   0.4960   0.09171   0.08373  -0.0420   0.4462   1.0000
   7.000   0.5098   0.09425   0.08625  -0.0421   0.4452   1.0000
   7.250   0.5170   0.09733   0.08934  -0.0423   0.4448   1.0000
   7.500   0.5131   0.09868   0.09067  -0.0411   0.4301   1.0000
   7.750   0.5726   0.09326   0.08510  -0.0380   0.3979   1.0000
   8.000   0.6582   0.08765   0.07936  -0.0361   0.3930   1.0000
   8.250   0.5927   0.09684   0.08866  -0.0372   0.3833   1.0000
   8.500   0.6337   0.09567   0.08746  -0.0362   0.3784   1.0000
   8.750   0.6174   0.10004   0.09186  -0.0364   0.3686   1.0000
   9.000   0.6473   0.09979   0.09158  -0.0356   0.3628   1.0000
   9.250   0.6995   0.09720   0.08894  -0.0341   0.3602   1.0000
   9.500   0.6715   0.10267   0.09448  -0.0347   0.3468   1.0000
   9.750   0.6716   0.10557   0.09739  -0.0346   0.3375   1.0000
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