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GOE 411 AIRFOIL (goe411-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 411 AIRFOIL (goe411-il)
Reynolds number: 50,000
Max Cl/Cd: 27.98 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe411-il-50000-n5.txt
Download as CSV file: xf-goe411-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 411 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.6461   0.09538   0.08815  -0.0423   1.0000   0.0301
 -12.250  -0.6682   0.08826   0.08092  -0.0464   1.0000   0.0297
 -12.000  -0.6895   0.08221   0.07472  -0.0496   1.0000   0.0294
 -11.750  -0.7096   0.07703   0.06939  -0.0516   1.0000   0.0291
 -11.500  -0.7291   0.07255   0.06469  -0.0525   1.0000   0.0288
 -11.250  -0.7464   0.06872   0.06066  -0.0523   1.0000   0.0287
 -11.000  -0.7623   0.06537   0.05706  -0.0511   1.0000   0.0285
 -10.750  -0.7754   0.06246   0.05391  -0.0491   1.0000   0.0283
 -10.500  -0.7845   0.05974   0.05096  -0.0465   1.0000   0.0282
 -10.250  -0.7908   0.05713   0.04809  -0.0436   1.0000   0.0281
 -10.000  -0.7932   0.05467   0.04537  -0.0406   1.0000   0.0281
  -9.750  -0.7908   0.05226   0.04272  -0.0379   1.0000   0.0282
  -9.500  -0.7822   0.04977   0.03997  -0.0357   1.0000   0.0284
  -9.250  -0.7690   0.04737   0.03738  -0.0341   1.0000   0.0290
  -9.000  -0.7531   0.04516   0.03499  -0.0327   1.0000   0.0302
  -8.750  -0.7354   0.04323   0.03287  -0.0313   1.0000   0.0315
  -8.500  -0.7176   0.04143   0.03077  -0.0297   1.0000   0.0330
  -8.250  -0.7048   0.03992   0.02909  -0.0273   1.0000   0.0336
  -8.000  -0.6976   0.03852   0.02753  -0.0242   1.0000   0.0343
  -7.750  -0.6940   0.03725   0.02612  -0.0206   1.0000   0.0349
  -7.500  -0.6908   0.03597   0.02467  -0.0169   1.0000   0.0355
  -7.250  -0.6900   0.03455   0.02316  -0.0130   1.0000   0.0366
  -7.000  -0.6890   0.03312   0.02164  -0.0091   1.0000   0.0386
  -6.750  -0.6846   0.03189   0.02029  -0.0056   1.0000   0.0411
  -6.500  -0.6778   0.03076   0.01899  -0.0022   1.0000   0.0444
  -6.250  -0.6708   0.02952   0.01769   0.0011   1.0000   0.0481
  -6.000  -0.6617   0.02840   0.01651   0.0041   1.0000   0.0539
  -5.750  -0.6573   0.02666   0.01517   0.0075   1.0000   0.0900
  -5.500  -0.6581   0.02476   0.01429   0.0115   1.0000   0.2435
  -5.250  -0.6527   0.02381   0.01380   0.0152   1.0000   0.3251
  -5.000  -0.6443   0.02322   0.01338   0.0188   1.0000   0.3868
  -4.750  -0.6357   0.02280   0.01312   0.0224   1.0000   0.4441
  -4.500  -0.6293   0.02249   0.01299   0.0267   1.0000   0.5040
  -4.250  -0.6184   0.02225   0.01282   0.0301   1.0000   0.5488
  -4.000  -0.6070   0.02209   0.01281   0.0339   1.0000   0.5985
  -3.750  -0.5879   0.02193   0.01259   0.0358   1.0000   0.6274
  -3.500  -0.5673   0.02179   0.01237   0.0373   1.0000   0.6518
  -3.250  -0.5466   0.02172   0.01217   0.0389   1.0000   0.6772
  -3.000  -0.5241   0.02174   0.01215   0.0402   1.0000   0.7031
  -2.750  -0.5015   0.02182   0.01218   0.0414   1.0000   0.7312
  -2.500  -0.4774   0.02198   0.01225   0.0424   1.0000   0.7607
  -2.250  -0.4503   0.02222   0.01244   0.0428   1.0000   0.7895
  -2.000  -0.4189   0.02255   0.01268   0.0423   1.0000   0.8157
  -1.750  -0.3875   0.02285   0.01288   0.0415   1.0000   0.8395
  -1.500  -0.3345   0.02337   0.01322   0.0363   0.9946   0.8578
  -1.250  -0.2778   0.02385   0.01354   0.0303   0.9869   0.8743
  -1.000  -0.2203   0.02424   0.01378   0.0240   0.9790   0.8887
  -0.750  -0.1637   0.02455   0.01397   0.0177   0.9702   0.9018
  -0.500  -0.1084   0.02476   0.01411   0.0117   0.9605   0.9146
  -0.250  -0.0541   0.02489   0.01418   0.0059   0.9501   0.9270
   0.000  -0.0002   0.02493   0.01421   0.0000   0.9390   0.9389
   0.250   0.0540   0.02488   0.01418  -0.0058   0.9271   0.9501
   0.500   0.1083   0.02476   0.01411  -0.0117   0.9147   0.9605
   0.750   0.1636   0.02454   0.01398  -0.0177   0.9018   0.9702
   1.000   0.2203   0.02423   0.01377  -0.0240   0.8887   0.9789
   1.250   0.2779   0.02384   0.01353  -0.0303   0.8743   0.9870
   1.500   0.3345   0.02336   0.01321  -0.0363   0.8578   0.9946
   1.750   0.3874   0.02285   0.01288  -0.0415   0.8395   1.0000
   2.000   0.4189   0.02254   0.01268  -0.0423   0.8157   1.0000
   2.250   0.4502   0.02222   0.01243  -0.0428   0.7896   1.0000
   2.500   0.4774   0.02197   0.01228  -0.0424   0.7607   1.0000
   2.750   0.5013   0.02182   0.01217  -0.0414   0.7312   1.0000
   3.000   0.5241   0.02174   0.01214  -0.0402   0.7032   1.0000
   3.250   0.5465   0.02171   0.01217  -0.0389   0.6771   1.0000
   3.500   0.5671   0.02179   0.01235  -0.0373   0.6518   1.0000
   3.750   0.5878   0.02192   0.01258  -0.0358   0.6274   1.0000
   4.000   0.6067   0.02208   0.01280  -0.0338   0.5979   1.0000
   4.250   0.6183   0.02224   0.01281  -0.0301   0.5488   1.0000
   4.500   0.6289   0.02248   0.01297  -0.0266   0.5030   1.0000
   4.750   0.6352   0.02280   0.01309  -0.0223   0.4428   1.0000
   5.000   0.6443   0.02322   0.01337  -0.0188   0.3869   1.0000
   5.250   0.6522   0.02382   0.01380  -0.0151   0.3221   1.0000
   5.500   0.6579   0.02477   0.01429  -0.0114   0.2425   1.0000
   6.000   0.6618   0.02838   0.01649  -0.0041   0.0540   1.0000
   6.250   0.6707   0.02953   0.01769  -0.0011   0.0480   1.0000
   6.500   0.6779   0.03074   0.01897   0.0022   0.0446   1.0000
   6.750   0.6850   0.03184   0.02024   0.0055   0.0417   1.0000
   7.000   0.6892   0.03310   0.02162   0.0091   0.0388   1.0000
   7.250   0.6907   0.03449   0.02310   0.0129   0.0368   1.0000
   7.500   0.6910   0.03595   0.02465   0.0169   0.0355   1.0000
   7.750   0.6944   0.03721   0.02608   0.0205   0.0349   1.0000
   8.000   0.6979   0.03851   0.02752   0.0241   0.0343   1.0000
   8.250   0.7049   0.03988   0.02905   0.0273   0.0337   1.0000
   8.500   0.7178   0.04142   0.03076   0.0296   0.0329   1.0000
   8.750   0.7354   0.04317   0.03281   0.0313   0.0317   1.0000
   9.000   0.7528   0.04510   0.03492   0.0327   0.0303   1.0000
   9.250   0.7688   0.04735   0.03733   0.0341   0.0289   1.0000
   9.500   0.7825   0.04982   0.04002   0.0356   0.0283   1.0000
   9.750   0.7911   0.05224   0.04270   0.0378   0.0282   1.0000
  10.000   0.7935   0.05466   0.04536   0.0405   0.0281   1.0000
  10.250   0.7912   0.05720   0.04816   0.0435   0.0281   1.0000
  10.500   0.7851   0.05978   0.05099   0.0464   0.0282   1.0000
  10.750   0.7761   0.06242   0.05387   0.0490   0.0283   1.0000
  11.000   0.7626   0.06543   0.05713   0.0510   0.0284   1.0000
  11.250   0.7471   0.06875   0.06068   0.0523   0.0286   1.0000
  11.500   0.7295   0.07259   0.06474   0.0525   0.0288   1.0000
  11.750   0.7100   0.07711   0.06946   0.0515   0.0291   1.0000
  12.000   0.6908   0.08212   0.07463   0.0495   0.0294   1.0000
  12.250   0.6687   0.08835   0.08100   0.0463   0.0297   1.0000
  12.500   0.6472   0.09537   0.08813   0.0421   0.0301   1.0000
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