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N-11 (n11-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: N-11 (n11-il)
Reynolds number: 500,000
Max Cl/Cd: 100.9 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n11-il-500000.txt
Download as CSV file: xf-n11-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: N-11                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3586   0.09415   0.09194  -0.0393   1.0000   0.0305
 -10.250  -0.3704   0.09137   0.08921  -0.0384   1.0000   0.0306
 -10.000  -0.3759   0.08508   0.08296  -0.0421   0.9980   0.0310
  -9.750  -0.3567   0.08266   0.08053  -0.0440   0.9959   0.0315
  -9.500  -0.3358   0.08001   0.07787  -0.0474   0.9937   0.0322
  -9.250  -0.3183   0.07634   0.07420  -0.0523   0.9886   0.0332
  -8.750  -0.2743   0.05155   0.04916  -0.0910   0.9735   0.0382
  -8.500  -0.2458   0.04981   0.04739  -0.0939   0.9716   0.0390
  -8.250  -0.2221   0.04764   0.04517  -0.0962   0.9656   0.0401
  -8.000  -0.2037   0.03526   0.03209  -0.1065   0.9573   0.0466
  -7.750  -0.1983   0.02400   0.01959  -0.1074   0.9451   0.0380
  -7.500  -0.1728   0.02218   0.01749  -0.1074   0.9384   0.0377
  -7.250  -0.1478   0.02063   0.01569  -0.1071   0.9306   0.0376
  -7.000  -0.1213   0.01941   0.01427  -0.1069   0.9234   0.0374
  -6.750  -0.0965   0.01756   0.01218  -0.1065   0.9151   0.0372
  -6.500  -0.0708   0.01622   0.01060  -0.1061   0.9066   0.0375
  -6.250  -0.0450   0.01439   0.00854  -0.1059   0.8986   0.0381
  -6.000  -0.0189   0.01342   0.00745  -0.1054   0.8887   0.0386
  -5.750   0.0082   0.01267   0.00659  -0.1051   0.8793   0.0390
  -5.500   0.0351   0.01207   0.00589  -0.1047   0.8691   0.0395
  -5.250   0.0618   0.01157   0.00533  -0.1043   0.8589   0.0401
  -5.000   0.0890   0.01116   0.00483  -0.1040   0.8499   0.0407
  -4.750   0.1160   0.01082   0.00443  -0.1036   0.8402   0.0418
  -4.500   0.1430   0.01053   0.00407  -0.1033   0.8309   0.0429
  -4.250   0.1703   0.01026   0.00371  -0.1029   0.8220   0.0438
  -4.000   0.1972   0.01001   0.00341  -0.1026   0.8122   0.0446
  -3.750   0.2245   0.00983   0.00315  -0.1023   0.8028   0.0454
  -3.500   0.2513   0.00953   0.00281  -0.1019   0.7927   0.0475
  -3.250   0.2786   0.00935   0.00261  -0.1016   0.7827   0.0504
  -3.000   0.3061   0.00924   0.00244  -0.1014   0.7736   0.0544
  -2.750   0.3332   0.00900   0.00230  -0.1011   0.7631   0.0742
  -2.500   0.3599   0.00871   0.00221  -0.1009   0.7527   0.1375
  -2.250   0.3870   0.00856   0.00215  -0.1007   0.7420   0.1843
  -2.000   0.4140   0.00840   0.00211  -0.1005   0.7302   0.2291
  -1.750   0.4407   0.00821   0.00206  -0.1003   0.7180   0.2872
  -1.500   0.4664   0.00784   0.00205  -0.1000   0.7054   0.4221
  -1.250   0.4885   0.00715   0.00210  -0.0990   0.6923   0.6740
  -1.000   0.5259   0.00658   0.00218  -0.1003   0.6779   0.9835
  -0.750   0.5643   0.00667   0.00215  -0.1026   0.6626   1.0000
  -0.500   0.5894   0.00679   0.00214  -0.1020   0.6480   1.0000
  -0.250   0.6145   0.00692   0.00216  -0.1014   0.6329   1.0000
   0.000   0.6396   0.00706   0.00219  -0.1008   0.6176   1.0000
   0.250   0.6649   0.00721   0.00223  -0.1002   0.6030   1.0000
   0.500   0.6902   0.00736   0.00228  -0.0996   0.5883   1.0000
   1.000   0.7410   0.00766   0.00241  -0.0987   0.5580   1.0000
   1.250   0.7665   0.00782   0.00250  -0.0982   0.5432   1.0000
   1.500   0.7917   0.00799   0.00259  -0.0977   0.5264   1.0000
   1.750   0.8170   0.00817   0.00268  -0.0972   0.5084   1.0000
   2.000   0.8422   0.00836   0.00280  -0.0968   0.4896   1.0000
   2.250   0.8667   0.00859   0.00293  -0.0962   0.4677   1.0000
   2.500   0.8908   0.00886   0.00307  -0.0956   0.4421   1.0000
   2.750   0.9144   0.00917   0.00325  -0.0949   0.4159   1.0000
   3.000   0.9384   0.00947   0.00344  -0.0943   0.3939   1.0000
   3.250   0.9626   0.00976   0.00364  -0.0938   0.3775   1.0000
   3.500   0.9869   0.01005   0.00386  -0.0933   0.3638   1.0000
   3.750   1.0114   0.01033   0.00408  -0.0928   0.3527   1.0000
   4.000   1.0357   0.01062   0.00432  -0.0923   0.3434   1.0000
   4.250   1.0608   0.01085   0.00454  -0.0920   0.3354   1.0000
   4.750   1.1100   0.01137   0.00503  -0.0912   0.3190   1.0000
   5.000   1.1337   0.01167   0.00530  -0.0906   0.3097   1.0000
   5.250   1.1583   0.01191   0.00554  -0.0903   0.3004   1.0000
   5.500   1.1825   0.01217   0.00580  -0.0898   0.2915   1.0000
   5.750   1.2060   0.01247   0.00607  -0.0893   0.2818   1.0000
   6.000   1.2305   0.01269   0.00632  -0.0889   0.2719   1.0000
   6.250   1.2539   0.01298   0.00659  -0.0884   0.2604   1.0000
   6.500   1.2767   0.01330   0.00689  -0.0878   0.2489   1.0000
   6.750   1.2991   0.01363   0.00719  -0.0871   0.2345   1.0000
   7.000   1.3205   0.01403   0.00754  -0.0863   0.2158   1.0000
   7.250   1.3400   0.01455   0.00795  -0.0852   0.1959   1.0000
   7.500   1.3584   0.01512   0.00844  -0.0840   0.1783   1.0000
   7.750   1.3763   0.01571   0.00896  -0.0827   0.1623   1.0000
   8.000   1.3919   0.01638   0.00954  -0.0810   0.1424   1.0000
   8.250   1.4012   0.01737   0.01031  -0.0783   0.1045   1.0000
   8.500   1.4061   0.01868   0.01138  -0.0751   0.0762   1.0000
   8.750   1.4139   0.01981   0.01239  -0.0724   0.0535   1.0000
   9.000   1.4127   0.02155   0.01389  -0.0686   0.0244   1.0000
   9.250   1.4217   0.02264   0.01502  -0.0663   0.0210   1.0000
   9.500   1.4330   0.02361   0.01607  -0.0644   0.0197   1.0000
   9.750   1.4430   0.02468   0.01723  -0.0625   0.0187   1.0000
  10.000   1.4507   0.02596   0.01860  -0.0605   0.0178   1.0000
  10.250   1.4547   0.02756   0.02029  -0.0583   0.0169   1.0000
  10.500   1.4594   0.02918   0.02202  -0.0563   0.0163   1.0000
  10.750   1.4658   0.03072   0.02366  -0.0548   0.0159   1.0000
  11.000   1.4703   0.03251   0.02556  -0.0533   0.0155   1.0000
  11.250   1.4729   0.03453   0.02768  -0.0519   0.0151   1.0000
  11.500   1.4738   0.03679   0.03004  -0.0506   0.0147   1.0000
  11.750   1.4731   0.03930   0.03266  -0.0494   0.0144   1.0000
  12.000   1.4702   0.04213   0.03559  -0.0485   0.0142   1.0000
  12.250   1.4652   0.04533   0.03890  -0.0477   0.0139   1.0000
  12.500   1.4580   0.04890   0.04258  -0.0472   0.0137   1.0000
  12.750   1.4487   0.05291   0.04670  -0.0470   0.0135   1.0000
  13.000   1.4374   0.05732   0.05123  -0.0470   0.0134   1.0000
  13.250   1.4254   0.06191   0.05593  -0.0471   0.0132   1.0000
  13.500   1.4189   0.06596   0.06008  -0.0474   0.0131   1.0000
  13.750   1.4163   0.06964   0.06387  -0.0479   0.0130   1.0000
  14.000   1.4127   0.07348   0.06782  -0.0485   0.0128   1.0000
  14.250   1.4088   0.07743   0.07188  -0.0493   0.0127   1.0000
  14.500   1.4044   0.08149   0.07604  -0.0500   0.0125   1.0000
  14.750   1.4000   0.08559   0.08024  -0.0509   0.0123   1.0000
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