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I.S.A. 961 (isa961-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: I.S.A. 961 (isa961-il)
Reynolds number: 500,000
Max Cl/Cd: 75.47 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-isa961-il-500000-n5.txt
Download as CSV file: xf-isa961-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: I.S.A. 961                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3623   0.08878   0.08662  -0.0348   1.0000   0.0066
  -9.750  -0.3728   0.08456   0.08245  -0.0350   1.0000   0.0066
  -9.250  -0.4163   0.02977   0.02665  -0.0941   0.9569   0.0062
  -9.000  -0.3920   0.02467   0.02098  -0.0976   0.9499   0.0063
  -8.750  -0.3662   0.02214   0.01806  -0.0989   0.9423   0.0064
  -8.500  -0.3412   0.01957   0.01511  -0.0999   0.9354   0.0066
  -8.250  -0.3152   0.01811   0.01342  -0.1002   0.9278   0.0068
  -8.000  -0.2880   0.01707   0.01220  -0.1005   0.9214   0.0071
  -7.750  -0.2615   0.01632   0.01131  -0.1004   0.9141   0.0074
  -7.500  -0.2346   0.01556   0.01039  -0.1004   0.9076   0.0079
  -7.250  -0.2081   0.01482   0.00949  -0.1002   0.9007   0.0083
  -7.000  -0.1816   0.01410   0.00857  -0.0999   0.8933   0.0087
  -6.750  -0.1552   0.01346   0.00777  -0.0995   0.8843   0.0090
  -6.500  -0.1285   0.01296   0.00711  -0.0991   0.8746   0.0093
  -6.250  -0.1025   0.01213   0.00613  -0.0987   0.8642   0.0100
  -6.000  -0.0757   0.01164   0.00553  -0.0984   0.8542   0.0106
  -5.750  -0.0487   0.01127   0.00504  -0.0980   0.8434   0.0115
  -5.500  -0.0217   0.01096   0.00460  -0.0977   0.8312   0.0126
  -5.250   0.0055   0.01069   0.00421  -0.0973   0.8181   0.0136
  -5.000   0.0327   0.01030   0.00368  -0.0969   0.8046   0.0157
  -4.750   0.0597   0.01002   0.00328  -0.0965   0.7888   0.0183
  -4.500   0.0861   0.00962   0.00290  -0.0961   0.7700   0.0370
  -4.250   0.1130   0.00957   0.00285  -0.0958   0.7483   0.0578
  -4.000   0.1402   0.00964   0.00279  -0.0954   0.7272   0.0649
  -3.750   0.1673   0.00966   0.00268  -0.0951   0.7065   0.0687
  -3.500   0.1942   0.00961   0.00253  -0.0948   0.6847   0.0722
  -3.250   0.2210   0.00962   0.00242  -0.0944   0.6619   0.0757
  -3.000   0.2476   0.00969   0.00233  -0.0941   0.6350   0.0790
  -2.750   0.2739   0.00975   0.00222  -0.0936   0.6035   0.0806
  -2.500   0.3000   0.00977   0.00209  -0.0932   0.5704   0.0826
  -2.250   0.3262   0.00984   0.00200  -0.0929   0.5362   0.0851
  -2.000   0.3513   0.01004   0.00197  -0.0923   0.4864   0.0874
  -1.750   0.3770   0.01022   0.00196  -0.0919   0.4471   0.0893
  -1.500   0.4033   0.01036   0.00195  -0.0916   0.4180   0.0914
  -1.250   0.4298   0.01049   0.00196  -0.0914   0.3932   0.0949
  -1.000   0.4564   0.01058   0.00199  -0.0911   0.3705   0.1032
  -0.750   0.4822   0.01074   0.00208  -0.0908   0.3365   0.1266
  -0.500   0.5074   0.01102   0.00218  -0.0905   0.2933   0.1437
  -0.250   0.5327   0.01131   0.00229  -0.0901   0.2554   0.1544
   0.000   0.5585   0.01153   0.00239  -0.0898   0.2296   0.1651
   0.250   0.5845   0.01172   0.00250  -0.0895   0.2100   0.1775
   0.500   0.6108   0.01186   0.00261  -0.0893   0.1937   0.1919
   0.750   0.6346   0.01230   0.00282  -0.0888   0.1333   0.2095
   1.000   0.6604   0.01244   0.00299  -0.0885   0.1230   0.2452
   1.250   0.6865   0.01249   0.00316  -0.0884   0.1167   0.3094
   1.500   0.7080   0.01158   0.00338  -0.0876   0.1132   0.7424
   2.000   0.7691   0.01148   0.00368  -0.0887   0.1084   1.0000
   2.250   0.7952   0.01167   0.00384  -0.0885   0.1062   1.0000
   2.500   0.8211   0.01188   0.00401  -0.0882   0.1039   1.0000
   2.750   0.8469   0.01209   0.00420  -0.0879   0.1015   1.0000
   3.000   0.8729   0.01228   0.00437  -0.0876   0.0997   1.0000
   3.250   0.8990   0.01244   0.00453  -0.0874   0.0984   1.0000
   3.500   0.9250   0.01262   0.00470  -0.0872   0.0963   1.0000
   3.750   0.9507   0.01282   0.00489  -0.0869   0.0931   1.0000
   4.000   0.9759   0.01306   0.00511  -0.0866   0.0886   1.0000
   4.250   1.0015   0.01327   0.00532  -0.0863   0.0837   1.0000
   4.500   1.0243   0.01376   0.00564  -0.0856   0.0598   1.0000
   4.750   1.0486   0.01407   0.00595  -0.0852   0.0580   1.0000
   5.000   1.0728   0.01438   0.00628  -0.0847   0.0565   1.0000
   5.250   1.0971   0.01469   0.00660  -0.0842   0.0553   1.0000
   5.500   1.1210   0.01501   0.00694  -0.0837   0.0539   1.0000
   5.750   1.1443   0.01537   0.00733  -0.0831   0.0515   1.0000
   6.000   1.1679   0.01569   0.00770  -0.0826   0.0498   1.0000
   6.250   1.1912   0.01602   0.00807  -0.0821   0.0481   1.0000
   6.500   1.2141   0.01638   0.00848  -0.0814   0.0462   1.0000
   6.750   1.2358   0.01683   0.00895  -0.0806   0.0437   1.0000
   7.000   1.2577   0.01724   0.00939  -0.0799   0.0413   1.0000
   7.250   1.2806   0.01753   0.00972  -0.0793   0.0375   1.0000
   7.500   1.2992   0.01818   0.01020  -0.0782   0.0171   1.0000
   7.750   1.3176   0.01883   0.01089  -0.0769   0.0122   1.0000
   8.000   1.3363   0.01941   0.01155  -0.0756   0.0108   1.0000
   8.250   1.3529   0.02011   0.01233  -0.0740   0.0095   1.0000
   8.500   1.3677   0.02082   0.01313  -0.0722   0.0085   1.0000
   8.750   1.3825   0.02144   0.01382  -0.0703   0.0078   1.0000
   9.000   1.3961   0.02214   0.01460  -0.0683   0.0072   1.0000
   9.250   1.4086   0.02294   0.01550  -0.0663   0.0068   1.0000
   9.500   1.4192   0.02389   0.01654  -0.0641   0.0063   1.0000
   9.750   1.4285   0.02497   0.01772  -0.0619   0.0060   1.0000
  10.000   1.4393   0.02596   0.01881  -0.0600   0.0058   1.0000
  10.250   1.4488   0.02707   0.02002  -0.0581   0.0055   1.0000
  10.500   1.4574   0.02830   0.02134  -0.0563   0.0053   1.0000
  10.750   1.4651   0.02963   0.02276  -0.0546   0.0050   1.0000
  11.000   1.4717   0.03110   0.02432  -0.0529   0.0047   1.0000
  11.250   1.4771   0.03273   0.02604  -0.0514   0.0045   1.0000
  11.500   1.4791   0.03473   0.02816  -0.0498   0.0044   1.0000
  11.750   1.4767   0.03726   0.03081  -0.0482   0.0042   1.0000
  12.000   1.4765   0.03971   0.03338  -0.0470   0.0041   1.0000
  12.250   1.4760   0.04232   0.03612  -0.0462   0.0040   1.0000
  12.500   1.4741   0.04521   0.03914  -0.0455   0.0040   1.0000
  12.750   1.4706   0.04843   0.04250  -0.0452   0.0039   1.0000
  13.000   1.4651   0.05206   0.04625  -0.0451   0.0038   1.0000
  13.250   1.4588   0.05594   0.05027  -0.0454   0.0037   1.0000
  13.500   1.4508   0.06025   0.05472  -0.0459   0.0037   1.0000
  13.750   1.4416   0.06493   0.05954  -0.0468   0.0036   1.0000
  14.000   1.4317   0.06989   0.06464  -0.0480   0.0036   1.0000
  14.250   1.4210   0.07514   0.07002  -0.0494   0.0035   1.0000
  14.500   1.4097   0.08062   0.07563  -0.0511   0.0035   1.0000
  14.750   1.3975   0.08636   0.08151  -0.0529   0.0035   1.0000
  15.000   1.3853   0.09216   0.08742  -0.0548   0.0034   1.0000
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