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WORTMANN FX 77-080 (fx77080-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 77-080 (fx77080-il)
Reynolds number: 100,000
Max Cl/Cd: 33.67 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx77080-il-100000.txt
Download as CSV file: xf-fx77080-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 77-080                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.6460   0.09155   0.08647   0.0015   1.0000   0.1489
  -8.750  -0.7860   0.05941   0.05377  -0.0219   1.0000   0.0702
  -8.500  -0.7853   0.05455   0.04876  -0.0211   1.0000   0.0687
  -8.250  -0.7872   0.04939   0.04328  -0.0199   1.0000   0.0673
  -8.000  -0.7871   0.04427   0.03769  -0.0181   1.0000   0.0664
  -7.750  -0.7817   0.04008   0.03299  -0.0161   1.0000   0.0671
  -7.500  -0.7722   0.03665   0.02897  -0.0140   1.0000   0.0692
  -7.250  -0.7595   0.03367   0.02529  -0.0117   1.0000   0.0710
  -7.000  -0.7430   0.03027   0.02159  -0.0101   1.0000   0.0730
  -6.750  -0.7229   0.02844   0.01967  -0.0089   1.0000   0.0773
  -6.500  -0.7028   0.02688   0.01767  -0.0072   1.0000   0.0835
  -6.250  -0.6812   0.02487   0.01566  -0.0061   1.0000   0.0895
  -6.000  -0.6592   0.02349   0.01396  -0.0047   1.0000   0.0981
  -5.750  -0.6373   0.02225   0.01272  -0.0035   1.0000   0.1095
  -5.500  -0.6155   0.02105   0.01147  -0.0022   1.0000   0.1244
  -5.250  -0.5943   0.01982   0.01037  -0.0009   1.0000   0.1436
  -5.000  -0.5733   0.01881   0.00935   0.0005   1.0000   0.1694
  -4.750  -0.5527   0.01793   0.00855   0.0019   1.0000   0.1979
  -4.500  -0.5319   0.01713   0.00790   0.0032   1.0000   0.2260
  -4.250  -0.5111   0.01643   0.00732   0.0046   1.0000   0.2552
  -4.000  -0.4901   0.01575   0.00677   0.0059   1.0000   0.2867
  -3.750  -0.4697   0.01500   0.00628   0.0074   1.0000   0.3222
  -3.500  -0.4501   0.01422   0.00579   0.0091   1.0000   0.3712
  -3.250  -0.4323   0.01334   0.00540   0.0112   1.0000   0.4476
  -3.000  -0.4169   0.01243   0.00517   0.0141   1.0000   0.5675
  -2.750  -0.3976   0.01181   0.00517   0.0171   1.0000   0.7042
  -2.500  -0.3657   0.01170   0.00534   0.0182   1.0000   0.8199
  -2.250  -0.3166   0.01197   0.00557   0.0157   1.0000   0.8976
  -2.000  -0.2499   0.01236   0.00574   0.0093   1.0000   0.9439
  -1.750  -0.1705   0.01261   0.00572  -0.0003   1.0000   0.9723
  -1.500  -0.0868   0.01250   0.00540  -0.0115   1.0000   0.9954
  -1.250  -0.0600   0.01224   0.00506  -0.0123   1.0000   1.0000
  -1.000  -0.0479   0.01202   0.00482  -0.0101   1.0000   1.0000
  -0.750  -0.0358   0.01186   0.00464  -0.0077   1.0000   1.0000
  -0.500  -0.0237   0.01175   0.00451  -0.0052   1.0000   1.0000
  -0.250  -0.0117   0.01168   0.00444  -0.0026   1.0000   1.0000
   0.000   0.0000   0.01166   0.00442   0.0000   1.0000   1.0000
   0.250   0.0118   0.01168   0.00444   0.0026   1.0000   1.0000
   0.500   0.0237   0.01175   0.00451   0.0052   1.0000   1.0000
   0.750   0.0359   0.01186   0.00464   0.0077   1.0000   1.0000
   1.000   0.0480   0.01202   0.00482   0.0101   1.0000   1.0000
   1.250   0.0601   0.01224   0.00506   0.0123   1.0000   1.0000
   1.500   0.0868   0.01250   0.00539   0.0115   0.9955   1.0000
   1.750   0.1703   0.01261   0.00572   0.0004   0.9724   1.0000
   2.000   0.2500   0.01236   0.00574  -0.0093   0.9437   1.0000
   2.250   0.3168   0.01196   0.00556  -0.0157   0.8966   1.0000
   2.500   0.3658   0.01170   0.00534  -0.0182   0.8198   1.0000
   2.750   0.3976   0.01181   0.00517  -0.0171   0.7044   1.0000
   3.000   0.4168   0.01244   0.00517  -0.0141   0.5659   1.0000
   3.250   0.4323   0.01334   0.00540  -0.0112   0.4472   1.0000
   3.500   0.4500   0.01423   0.00580  -0.0090   0.3707   1.0000
   3.750   0.4696   0.01500   0.00628  -0.0074   0.3218   1.0000
   4.000   0.4900   0.01574   0.00677  -0.0059   0.2864   1.0000
   4.250   0.5111   0.01644   0.00733  -0.0046   0.2551   1.0000
   4.500   0.5320   0.01715   0.00791  -0.0032   0.2263   1.0000
   4.750   0.5528   0.01794   0.00856  -0.0019   0.1981   1.0000
   5.000   0.5733   0.01881   0.00936  -0.0005   0.1697   1.0000
   5.250   0.5943   0.01982   0.01037   0.0009   0.1437   1.0000
   5.500   0.6154   0.02099   0.01143   0.0022   0.1239   1.0000
   5.750   0.6374   0.02226   0.01273   0.0035   0.1096   1.0000
   6.000   0.6592   0.02349   0.01397   0.0047   0.0982   1.0000
   6.250   0.6812   0.02487   0.01566   0.0062   0.0893   1.0000
   6.500   0.7026   0.02684   0.01765   0.0073   0.0833   1.0000
   6.750   0.7229   0.02836   0.01956   0.0089   0.0769   1.0000
   7.000   0.7430   0.03028   0.02158   0.0101   0.0728   1.0000
   7.250   0.7593   0.03367   0.02531   0.0117   0.0709   1.0000
   7.500   0.7721   0.03664   0.02898   0.0140   0.0690   1.0000
   7.750   0.7816   0.04006   0.03298   0.0161   0.0668   1.0000
   8.000   0.7866   0.04437   0.03781   0.0182   0.0660   1.0000
   8.250   0.7872   0.04941   0.04329   0.0199   0.0673   1.0000
   8.500   0.7852   0.05459   0.04880   0.0211   0.0687   1.0000
   8.750   0.7851   0.05954   0.05390   0.0219   0.0701   1.0000
   9.000   0.6363   0.05597   0.05121   0.0234   0.0785   1.0000
   9.250   0.6029   0.06538   0.06065   0.0179   0.0868   1.0000
   9.500   0.6121   0.06798   0.06325   0.0198   0.0853   1.0000
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