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I.S.A. 960 (isa960-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: I.S.A. 960 (isa960-il)
Reynolds number: 50,000
Max Cl/Cd: 39.26 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-isa960-il-50000.txt
Download as CSV file: xf-isa960-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: I.S.A. 960                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3298   0.10300   0.09659  -0.0255   1.0000   0.1846
  -8.750  -0.3443   0.10224   0.09599  -0.0255   1.0000   0.1898
  -8.500  -0.3703   0.10270   0.09667  -0.0265   1.0000   0.1913
  -8.250  -0.3426   0.09639   0.09033  -0.0226   1.0000   0.2020
  -8.000  -0.3647   0.09620   0.09034  -0.0231   1.0000   0.2060
  -7.750  -0.3549   0.09197   0.08617  -0.0200   1.0000   0.2128
  -7.500  -0.3668   0.09072   0.08504  -0.0195   1.0000   0.2202
  -7.250  -0.3755   0.08845   0.08289  -0.0189   1.0000   0.2247
  -7.000  -0.3736   0.08577   0.08027  -0.0160   1.0000   0.2331
  -6.750  -0.3854   0.08411   0.07870  -0.0174   1.0000   0.2397
  -6.500  -0.3817   0.08116   0.07579  -0.0138   1.0000   0.2477
  -6.250  -0.3861   0.07883   0.07352  -0.0143   1.0000   0.2567
  -6.000  -0.3870   0.07683   0.07153  -0.0159   1.0000   0.2700
  -5.750  -0.3841   0.07440   0.06911  -0.0157   1.0000   0.2850
  -5.500  -0.3809   0.07143   0.06620  -0.0131   1.0000   0.3013
  -5.250  -0.3775   0.06864   0.06348  -0.0096   1.0000   0.3199
  -5.000  -0.3731   0.06624   0.06110  -0.0089   1.0000   0.3481
  -4.750  -0.3688   0.06379   0.05870  -0.0065   1.0000   0.3789
  -4.000  -0.1954   0.04329   0.03563  -0.0488   1.0000   0.1752
  -3.750  -0.1675   0.04039   0.03244  -0.0504   1.0000   0.1786
  -3.500  -0.1399   0.03825   0.02999  -0.0516   1.0000   0.1863
  -3.250  -0.1081   0.03584   0.02704  -0.0533   1.0000   0.1947
  -3.000  -0.0821   0.03445   0.02543  -0.0539   1.0000   0.2141
  -2.750  -0.0539   0.03325   0.02379  -0.0548   1.0000   0.2374
  -2.500  -0.0325   0.03273   0.02330  -0.0548   1.0000   0.2665
  -2.250  -0.0064   0.03219   0.02253  -0.0556   0.9994   0.2856
  -2.000   0.0749   0.03125   0.02126  -0.0656   0.9776   0.3101
  -1.750   0.1328   0.03075   0.02044  -0.0712   0.9626   0.3308
  -1.500   0.1853   0.03019   0.01985  -0.0757   0.9486   0.3632
  -1.250   0.2355   0.02948   0.01933  -0.0797   0.9346   0.4098
  -1.000   0.2769   0.02725   0.01887  -0.0812   0.9228   0.6891
  -0.750   0.3275   0.02717   0.01814  -0.0845   0.9044   1.0000
  -0.500   0.3755   0.02723   0.01783  -0.0876   0.8876   1.0000
  -0.250   0.4193   0.02726   0.01760  -0.0900   0.8719   1.0000
   0.000   0.4614   0.02721   0.01737  -0.0919   0.8567   1.0000
   0.250   0.5021   0.02702   0.01704  -0.0933   0.8410   1.0000
   0.500   0.5412   0.02669   0.01660  -0.0941   0.8250   1.0000
   0.750   0.5789   0.02625   0.01607  -0.0945   0.8089   1.0000
   1.000   0.6136   0.02587   0.01563  -0.0944   0.7934   1.0000
   1.250   0.6448   0.02567   0.01538  -0.0940   0.7786   1.0000
   1.500   0.6743   0.02556   0.01524  -0.0935   0.7642   1.0000
   1.750   0.7046   0.02536   0.01501  -0.0929   0.7492   1.0000
   2.000   0.7349   0.02509   0.01473  -0.0921   0.7336   1.0000
   2.250   0.7647   0.02486   0.01448  -0.0913   0.7176   1.0000
   2.500   0.7905   0.02489   0.01451  -0.0902   0.7002   1.0000
   2.750   0.8155   0.02498   0.01464  -0.0890   0.6819   1.0000
   3.000   0.8410   0.02503   0.01472  -0.0879   0.6631   1.0000
   3.250   0.8674   0.02501   0.01471  -0.0868   0.6438   1.0000
   3.500   0.8933   0.02500   0.01470  -0.0856   0.6235   1.0000
   3.750   0.9167   0.02512   0.01489  -0.0843   0.6003   1.0000
   4.000   0.9427   0.02514   0.01488  -0.0831   0.5776   1.0000
   4.250   0.9678   0.02529   0.01498  -0.0819   0.5532   1.0000
   4.500   0.9917   0.02556   0.01520  -0.0806   0.5270   1.0000
   4.750   1.0168   0.02590   0.01542  -0.0795   0.5026   1.0000
   5.000   1.0400   0.02654   0.01603  -0.0786   0.4792   1.0000
   5.250   1.0654   0.02716   0.01654  -0.0778   0.4590   1.0000
   5.500   1.0859   0.02794   0.01738  -0.0766   0.4364   1.0000
   5.750   1.1088   0.02870   0.01810  -0.0756   0.4167   1.0000
   6.000   1.1328   0.02950   0.01881  -0.0748   0.3981   1.0000
   6.250   1.1536   0.03056   0.01994  -0.0738   0.3788   1.0000
   6.500   1.1759   0.03169   0.02112  -0.0729   0.3607   1.0000
   6.750   1.1993   0.03299   0.02243  -0.0722   0.3450   1.0000
   7.000   1.2233   0.03447   0.02396  -0.0718   0.3323   1.0000
   7.250   1.2499   0.03592   0.02539  -0.0717   0.3225   1.0000
   7.500   1.2696   0.03773   0.02751  -0.0709   0.3139   1.0000
   7.750   1.2956   0.03941   0.02926  -0.0709   0.3078   1.0000
   8.000   1.3104   0.04175   0.03202  -0.0698   0.3030   1.0000
   8.250   1.3281   0.04403   0.03461  -0.0690   0.2992   1.0000
   8.500   1.3481   0.04629   0.03715  -0.0685   0.2960   1.0000
   8.750   1.3612   0.04893   0.04011  -0.0673   0.2926   1.0000
   9.000   1.3583   0.05235   0.04402  -0.0648   0.2889   1.0000
   9.250   1.3843   0.05299   0.04469  -0.0642   0.2775   1.0000
   9.500   1.3998   0.05341   0.04517  -0.0625   0.2619   1.0000
   9.750   1.4096   0.05364   0.04549  -0.0601   0.2443   1.0000
  10.000   1.4313   0.05190   0.04354  -0.0584   0.2197   1.0000
  10.250   1.2735   0.07349   0.06641  -0.0513   0.2696   1.0000
  10.500   1.2514   0.07892   0.07193  -0.0503   0.2664   1.0000
  10.750   1.2265   0.08578   0.07885  -0.0506   0.2645   1.0000
  11.000   1.2433   0.08448   0.07770  -0.0478   0.2472   1.0000
  11.500   1.4230   0.06320   0.05415  -0.0388   0.1069   1.0000
  11.750   1.4043   0.06701   0.05838  -0.0354   0.1040   1.0000
  12.000   1.3830   0.07096   0.06273  -0.0328   0.1020   1.0000
  12.250   1.3660   0.07532   0.06739  -0.0311   0.0992   1.0000
  12.500   1.3636   0.07983   0.07198  -0.0302   0.0944   1.0000
  12.750   1.3377   0.08486   0.07733  -0.0296   0.0941   1.0000
  13.000   1.3115   0.09056   0.08330  -0.0300   0.0942   1.0000
  13.250   1.2852   0.09693   0.08992  -0.0314   0.0944   1.0000
  13.500   1.2585   0.10400   0.09719  -0.0336   0.0948   1.0000
  13.750   1.2327   0.11172   0.10508  -0.0367   0.0953   1.0000
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