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FX 66-H-80 (fx66h80-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 66-H-80 (fx66h80-il)
Reynolds number: 100,000
Max Cl/Cd: 47.52 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx66h80-il-100000.txt
Download as CSV file: xf-fx66h80-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 66-H-80                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5597   0.11133   0.10704   0.0235   1.0000   0.0600
  -8.500  -0.5642   0.10864   0.10442   0.0188   1.0000   0.0604
  -8.250  -0.5700   0.10570   0.10156   0.0139   1.0000   0.0607
  -8.000  -0.5728   0.10263   0.09848   0.0090   1.0000   0.0609
  -7.750  -0.5451   0.09471   0.09062   0.0177   1.0000   0.0644
  -7.500  -0.5416   0.09113   0.08709   0.0164   1.0000   0.0665
  -7.250  -0.5397   0.08752   0.08352   0.0140   1.0000   0.0685
  -7.000  -0.5361   0.08369   0.07970   0.0100   1.0000   0.0713
  -6.750  -0.5327   0.08083   0.07668   0.0019   1.0000   0.0740
  -6.500  -0.5251   0.07558   0.07141   0.0001   1.0000   0.0753
  -6.250  -0.5125   0.07112   0.06710   0.0024   1.0000   0.0783
  -6.000  -0.4999   0.06753   0.06347   0.0012   1.0000   0.0827
  -5.750  -0.4866   0.06392   0.05951  -0.0036   1.0000   0.0890
  -5.500  -0.4724   0.05961   0.05539  -0.0024   1.0000   0.0926
  -5.250  -0.4550   0.05664   0.05205  -0.0050   1.0000   0.1027
  -5.000  -0.4388   0.05251   0.04808  -0.0044   1.0000   0.1080
  -4.750  -0.4205   0.04916   0.04463  -0.0053   1.0000   0.1200
  -4.500  -0.4012   0.04622   0.04167  -0.0059   1.0000   0.1372
  -4.250  -0.3808   0.04319   0.03862  -0.0071   1.0000   0.1610
  -4.000  -0.3433   0.04000   0.03520  -0.0114   0.9032   0.2002
  -3.250  -0.2986   0.03380   0.02852  -0.0046   0.7885   0.3104
  -3.000  -0.2255   0.02742   0.01948  -0.0055   0.7736   0.0724
  -2.750  -0.1984   0.02490   0.01630  -0.0037   0.7548   0.0628
  -2.500  -0.1714   0.02355   0.01448  -0.0023   0.7378   0.0600
  -2.250  -0.1444   0.02185   0.01245  -0.0013   0.7229   0.0594
  -2.000  -0.1169   0.02046   0.01080  -0.0004   0.7088   0.0620
  -1.750  -0.0905   0.01932   0.00962   0.0002   0.6957   0.0712
  -1.500   0.0236   0.01328   0.00682  -0.0142   0.6790   1.0000
  -1.250   0.0483   0.01341   0.00635  -0.0133   0.6681   1.0000
  -1.000   0.0732   0.01354   0.00616  -0.0127   0.6567   1.0000
  -0.750   0.0980   0.01369   0.00605  -0.0122   0.6463   1.0000
  -0.500   0.1225   0.01387   0.00597  -0.0115   0.6372   1.0000
  -0.250   0.1471   0.01405   0.00593  -0.0109   0.6283   1.0000
   0.000   0.1723   0.01426   0.00596  -0.0105   0.6192   1.0000
   0.250   0.1968   0.01448   0.00599  -0.0099   0.6116   1.0000
   0.500   0.2220   0.01471   0.00611  -0.0095   0.6030   1.0000
   0.750   0.2470   0.01497   0.00626  -0.0090   0.5955   1.0000
   1.000   0.2719   0.01523   0.00640  -0.0085   0.5881   1.0000
   1.250   0.2972   0.01553   0.00664  -0.0082   0.5805   1.0000
   1.500   0.3219   0.01581   0.00683  -0.0077   0.5738   1.0000
   1.750   0.3474   0.01616   0.00717  -0.0074   0.5666   1.0000
   2.000   0.3721   0.01647   0.00743  -0.0069   0.5601   1.0000
   2.250   0.3974   0.01686   0.00784  -0.0067   0.5529   1.0000
   2.500   0.4222   0.01721   0.00816  -0.0062   0.5467   1.0000
   2.750   0.4475   0.01766   0.00865  -0.0060   0.5402   1.0000
   3.000   0.4723   0.01805   0.00905  -0.0055   0.5337   1.0000
   3.250   0.4972   0.01853   0.00961  -0.0052   0.5276   1.0000
   3.500   0.5223   0.01903   0.01018  -0.0050   0.5211   1.0000
   3.750   0.5467   0.01947   0.01063  -0.0044   0.5159   1.0000
   4.000   0.5718   0.02010   0.01143  -0.0044   0.5084   1.0000
   4.250   0.5962   0.02053   0.01187  -0.0037   0.5038   1.0000
   4.500   0.6209   0.02135   0.01298  -0.0039   0.4963   1.0000
   4.750   0.6453   0.02181   0.01348  -0.0033   0.4911   1.0000
   5.000   0.6694   0.02272   0.01463  -0.0034   0.4842   1.0000
   5.250   0.6936   0.02330   0.01533  -0.0028   0.4784   1.0000
   5.500   0.7173   0.02417   0.01641  -0.0027   0.4720   1.0000
   5.750   0.7410   0.02489   0.01738  -0.0023   0.4652   1.0000
   6.000   0.7643   0.02571   0.01842  -0.0019   0.4585   1.0000
   6.250   0.7885   0.02573   0.01856  -0.0006   0.4496   1.0000
   6.500   0.8128   0.02318   0.01588   0.0030   0.4231   1.0000
   6.750   0.8368   0.02056   0.01314   0.0061   0.3884   1.0000
   7.000   0.8602   0.01810   0.01080   0.0086   0.3173   1.0000
   7.250   0.8627   0.02211   0.01320   0.0096   0.0801   1.0000
   7.500   0.8758   0.02439   0.01556   0.0107   0.0658   1.0000
   7.750   0.8888   0.02627   0.01752   0.0121   0.0568   1.0000
   8.000   0.8992   0.02836   0.01948   0.0140   0.0508   1.0000
   8.250   0.9175   0.03002   0.02120   0.0159   0.0479   1.0000
   8.500   0.9386   0.03211   0.02331   0.0177   0.0456   1.0000
   8.750   0.9590   0.03445   0.02571   0.0189   0.0427   1.0000
   9.000   0.9791   0.03882   0.03004   0.0198   0.0396   1.0000
   9.250   0.9962   0.04164   0.03324   0.0209   0.0391   1.0000
   9.500   1.0119   0.04589   0.03779   0.0219   0.0396   1.0000
   9.750   1.0266   0.04878   0.04105   0.0231   0.0404   1.0000
  10.000   1.0313   0.05109   0.04415   0.0249   0.0428   1.0000
  10.250   1.0256   0.05548   0.04912   0.0260   0.0456   1.0000
  10.500   1.0195   0.05994   0.05391   0.0266   0.0478   1.0000
  10.750   1.0139   0.06493   0.05909   0.0268   0.0498   1.0000
  11.000   0.9074   0.05713   0.05167   0.0288   0.0470   1.0000
  11.250   1.0039   0.07672   0.07139   0.0268   0.0642   1.0000
  11.500   0.9796   0.08043   0.07526   0.0247   0.0644   1.0000
  11.750   0.9551   0.08559   0.08053   0.0210   0.0644   1.0000
  12.000   0.9336   0.09138   0.08634   0.0168   0.0643   1.0000
  12.250   0.9102   0.09815   0.09319   0.0117   0.0642   1.0000
  12.500   0.8856   0.10582   0.10089   0.0059   0.0642   1.0000
  12.750   0.8589   0.11476   0.10986  -0.0011   0.0643   1.0000
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