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FX 61-140 AIRFOIL (fx61140-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 61-140 AIRFOIL (fx61140-il)
Reynolds number: 200,000
Max Cl/Cd: 69.25 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx61140-il-200000.txt
Download as CSV file: xf-fx61140-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 61-140 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4117   0.08910   0.08580  -0.0440   1.0000   0.0481
  -9.250  -0.4251   0.08255   0.07931  -0.0486   1.0000   0.0501
  -9.000  -0.4381   0.07681   0.07362  -0.0515   1.0000   0.0485
  -8.750  -0.4608   0.07149   0.06831  -0.0538   1.0000   0.0477
  -8.500  -0.4876   0.06783   0.06464  -0.0536   1.0000   0.0475
  -8.250  -0.5177   0.06518   0.06201  -0.0513   1.0000   0.0465
  -8.000  -0.5374   0.06221   0.05899  -0.0504   1.0000   0.0474
  -7.750  -0.5531   0.05955   0.05624  -0.0487   1.0000   0.0488
  -7.500  -0.5653   0.05699   0.05353  -0.0470   1.0000   0.0501
  -7.250  -0.5696   0.05343   0.04920  -0.0504   0.9965   0.0539
  -7.000  -0.5418   0.04853   0.04465  -0.0529   0.9935   0.0578
  -6.750  -0.5085   0.04405   0.03958  -0.0597   0.9863   0.0685
  -6.500  -0.4757   0.04056   0.03608  -0.0629   0.9804   0.0731
  -6.250  -0.4386   0.03681   0.03197  -0.0679   0.9746   0.0846
  -6.000  -0.4033   0.03380   0.02871  -0.0717   0.9672   0.0983
  -5.750  -0.3529   0.02489   0.01811  -0.0682   0.9645   0.0286
  -5.250  -0.2772   0.02093   0.01373  -0.0714   0.9514   0.0298
  -5.000  -0.2387   0.01885   0.01174  -0.0738   0.9470   0.0345
  -4.750  -0.2039   0.01752   0.01037  -0.0750   0.9368   0.0377
  -4.500  -0.1635   0.01589   0.00874  -0.0779   0.9290   0.0443
  -4.250  -0.1181   0.01448   0.00731  -0.0821   0.9211   0.0645
  -4.000  -0.0616   0.01118   0.00649  -0.0911   0.9141   0.5855
  -3.750  -0.0201   0.01167   0.00688  -0.0925   0.9016   0.6285
  -3.500   0.0164   0.01259   0.00772  -0.0923   0.8851   0.6556
  -3.250   0.0468   0.01385   0.00893  -0.0900   0.8659   0.6739
  -3.000   0.0800   0.01452   0.00943  -0.0895   0.8450   0.6853
  -2.750   0.1164   0.01462   0.00928  -0.0911   0.8222   0.6956
  -2.500   0.1424   0.01491   0.00942  -0.0898   0.8005   0.6989
  -2.250   0.1694   0.01510   0.00942  -0.0891   0.7798   0.7046
  -2.000   0.1991   0.01512   0.00922  -0.0896   0.7614   0.7116
  -1.750   0.2226   0.01530   0.00926  -0.0882   0.7438   0.7154
  -1.500   0.2546   0.01522   0.00899  -0.0898   0.7270   0.7240
  -1.250   0.2767   0.01536   0.00902  -0.0881   0.7124   0.7267
  -1.000   0.3012   0.01546   0.00901  -0.0871   0.6987   0.7308
  -0.750   0.3337   0.01541   0.00878  -0.0888   0.6855   0.7384
  -0.500   0.3564   0.01551   0.00878  -0.0874   0.6741   0.7411
  -0.250   0.3809   0.01556   0.00877  -0.0866   0.6620   0.7451
   0.000   0.4128   0.01554   0.00864  -0.0881   0.6506   0.7517
   0.250   0.4369   0.01559   0.00862  -0.0872   0.6407   0.7549
   0.500   0.4619   0.01566   0.00862  -0.0865   0.6314   0.7585
   0.750   0.4906   0.01568   0.00860  -0.0871   0.6213   0.7638
   1.000   0.5195   0.01571   0.00855  -0.0876   0.6125   0.7681
   1.250   0.5438   0.01576   0.00858  -0.0868   0.6040   0.7712
   1.500   0.5710   0.01582   0.00861  -0.0869   0.5956   0.7754
   1.750   0.6054   0.01589   0.00857  -0.0889   0.5876   0.7807
   2.000   0.6282   0.01590   0.00863  -0.0878   0.5793   0.7832
   2.250   0.6544   0.01601   0.00869  -0.0875   0.5725   0.7866
   2.500   0.6821   0.01605   0.00878  -0.0878   0.5639   0.7908
   2.750   0.7154   0.01616   0.00882  -0.0895   0.5567   0.7951
   3.000   0.7384   0.01619   0.00893  -0.0885   0.5489   0.7978
   3.250   0.7648   0.01631   0.00902  -0.0883   0.5424   0.8011
   3.500   0.7930   0.01639   0.00917  -0.0887   0.5345   0.8049
   3.750   0.8261   0.01656   0.00929  -0.0903   0.5277   0.8091
   4.000   0.8492   0.01661   0.00946  -0.0894   0.5202   0.8117
   4.250   0.8764   0.01677   0.00959  -0.0894   0.5143   0.8147
   4.500   0.9032   0.01688   0.00982  -0.0895   0.5064   0.8184
   4.750   0.9356   0.01710   0.01000  -0.0908   0.5000   0.8222
   5.000   0.9606   0.01718   0.01025  -0.0905   0.4921   0.8250
   5.500   1.0125   0.01747   0.01068  -0.0901   0.4776   0.8312
   5.750   1.0430   0.01770   0.01090  -0.0910   0.4710   0.8347
   6.000   1.0707   0.01785   0.01124  -0.0914   0.4625   0.8377
   6.250   1.0955   0.01798   0.01141  -0.0908   0.4548   0.8404
   6.500   1.1196   0.01802   0.01154  -0.0902   0.4448   0.8437
   6.750   1.1445   0.01806   0.01169  -0.0899   0.4329   0.8471
   7.000   1.1705   0.01804   0.01174  -0.0899   0.4185   0.8503
   7.250   1.1921   0.01800   0.01181  -0.0888   0.4039   0.8532
   7.500   1.2133   0.01803   0.01194  -0.0877   0.3896   0.8565
   7.750   1.2362   0.01814   0.01216  -0.0870   0.3752   0.8598
   8.000   1.2600   0.01831   0.01242  -0.0866   0.3593   0.8631
   8.250   1.2812   0.01850   0.01270  -0.0857   0.3389   0.8664
   8.500   1.2971   0.01877   0.01298  -0.0838   0.3097   0.8697
   8.750   1.3104   0.01938   0.01350  -0.0818   0.2648   0.8732
   9.000   1.3165   0.02071   0.01445  -0.0791   0.1960   0.8769
   9.250   1.3111   0.02274   0.01598  -0.0750   0.1248   0.8806
   9.500   1.3034   0.02465   0.01761  -0.0704   0.0824   0.8846
   9.750   1.3001   0.02659   0.01940  -0.0669   0.0583   0.8886
  10.000   1.2995   0.02856   0.02139  -0.0642   0.0442   0.8925
  10.250   1.2910   0.03084   0.02371  -0.0607   0.0351   0.8967
  10.500   1.2819   0.03353   0.02650  -0.0581   0.0281   0.9016
  10.750   1.2719   0.03683   0.02997  -0.0564   0.0245   0.9063
  11.000   1.2668   0.03967   0.03295  -0.0551   0.0222   0.9108
  11.250   1.2613   0.04288   0.03628  -0.0544   0.0206   0.9158
  11.500   1.2530   0.04672   0.04022  -0.0542   0.0194   0.9207
  11.750   1.2421   0.05058   0.04417  -0.0532   0.0184   0.9261
  12.000   1.2461   0.05307   0.04682  -0.0530   0.0175   0.9333
  12.250   1.2465   0.05564   0.04953  -0.0524   0.0164   0.9425
  12.500   1.2458   0.05826   0.05229  -0.0519   0.0155   0.9587
  12.750   1.2475   0.06126   0.05540  -0.0523   0.0147   1.0000
  13.000   1.2530   0.06445   0.05871  -0.0531   0.0141   1.0000
  13.250   1.2590   0.06756   0.06190  -0.0535   0.0136   1.0000
  13.500   1.2663   0.07060   0.06502  -0.0534   0.0130   1.0000
  13.750   1.2756   0.07379   0.06836  -0.0525   0.0127   1.0000
  14.000   1.2802   0.07797   0.07276  -0.0523   0.0125   1.0000
  14.250   1.2796   0.08245   0.07748  -0.0538   0.0124   1.0000
  14.500   1.2768   0.08735   0.08262  -0.0555   0.0124   1.0000
  14.750   1.2703   0.09281   0.08833  -0.0577   0.0124   1.0000
  15.000   1.2632   0.09863   0.09437  -0.0600   0.0124   1.0000
  15.250   1.2530   0.10499   0.10097  -0.0630   0.0125   1.0000
  15.500   1.2428   0.11142   0.10764  -0.0665   0.0125   1.0000
  15.750   1.2343   0.11762   0.11404  -0.0704   0.0126   1.0000
  16.000   1.2263   0.12395   0.12055  -0.0747   0.0127   1.0000
  16.250   1.2135   0.13150   0.12831  -0.0798   0.0127   1.0000
  16.500   1.2038   0.13872   0.13571  -0.0851   0.0128   1.0000
  16.750   1.1926   0.14666   0.14385  -0.0911   0.0130   1.0000
  17.000   1.1749   0.15685   0.15429  -0.0988   0.0133   1.0000
  17.250   0.8665   0.17032   0.16851  -0.0926   0.0163   0.9241
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