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N-11 (n11-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: N-11 (n11-il)
Reynolds number: 500,000
Max Cl/Cd: 93.9 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n11-il-500000-n5.txt
Download as CSV file: xf-n11-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.3919   0.09491   0.09256  -0.0417   1.0000   0.0161
 -11.500  -0.3906   0.09275   0.09043  -0.0417   1.0000   0.0163
 -11.000  -0.5417   0.02918   0.02558  -0.1022   0.9755   0.0201
 -10.750  -0.5180   0.02709   0.02331  -0.1037   0.9710   0.0205
 -10.500  -0.4902   0.02635   0.02253  -0.1044   0.9653   0.0209
 -10.250  -0.4594   0.02561   0.02171  -0.1058   0.9614   0.0213
 -10.000  -0.4366   0.02471   0.02069  -0.1056   0.9532   0.0218
  -9.750  -0.4098   0.02342   0.01921  -0.1063   0.9480   0.0223
  -9.500  -0.3873   0.02223   0.01783  -0.1060   0.9391   0.0229
  -9.250  -0.3607   0.02106   0.01644  -0.1064   0.9324   0.0237
  -9.000  -0.3369   0.02002   0.01517  -0.1060   0.9222   0.0243
  -8.750  -0.3111   0.01902   0.01396  -0.1060   0.9126   0.0247
  -8.500  -0.2845   0.01823   0.01296  -0.1059   0.9023   0.0251
  -8.250  -0.2577   0.01772   0.01228  -0.1057   0.8905   0.0254
  -8.000  -0.2338   0.01606   0.01039  -0.1055   0.8790   0.0261
  -7.750  -0.2077   0.01527   0.00945  -0.1052   0.8681   0.0265
  -7.500  -0.1813   0.01466   0.00870  -0.1050   0.8582   0.0269
  -7.250  -0.1548   0.01412   0.00805  -0.1047   0.8486   0.0273
  -7.000  -0.1281   0.01364   0.00746  -0.1045   0.8401   0.0278
  -6.750  -0.1012   0.01324   0.00695  -0.1042   0.8318   0.0284
  -6.500  -0.0742   0.01284   0.00646  -0.1040   0.8247   0.0290
  -6.250  -0.0473   0.01244   0.00595  -0.1037   0.8168   0.0294
  -6.000  -0.0204   0.01206   0.00548  -0.1034   0.8083   0.0298
  -5.750   0.0064   0.01174   0.00505  -0.1031   0.7991   0.0302
  -5.500   0.0335   0.01142   0.00467  -0.1029   0.7906   0.0305
  -5.250   0.0606   0.01115   0.00432  -0.1026   0.7825   0.0309
  -5.000   0.0878   0.01089   0.00400  -0.1024   0.7735   0.0312
  -4.750   0.1150   0.01066   0.00370  -0.1021   0.7647   0.0316
  -4.500   0.1423   0.01045   0.00344  -0.1019   0.7550   0.0319
  -4.250   0.1696   0.01024   0.00317  -0.1017   0.7448   0.0324
  -4.000   0.1965   0.00998   0.00285  -0.1014   0.7339   0.0336
  -3.750   0.2238   0.00981   0.00263  -0.1012   0.7216   0.0345
  -3.500   0.2509   0.00968   0.00244  -0.1009   0.7067   0.0354
  -3.250   0.2777   0.00961   0.00227  -0.1006   0.6894   0.0364
  -3.000   0.3045   0.00955   0.00213  -0.1003   0.6723   0.0376
  -2.750   0.3315   0.00951   0.00201  -0.1000   0.6579   0.0390
  -2.500   0.3586   0.00949   0.00193  -0.0998   0.6443   0.0410
  -2.250   0.3857   0.00943   0.00185  -0.0996   0.6312   0.0485
  -2.000   0.4124   0.00932   0.00182  -0.0994   0.6182   0.0842
  -1.750   0.4392   0.00926   0.00180  -0.0992   0.6054   0.1144
  -1.500   0.4659   0.00918   0.00181  -0.0990   0.5929   0.1559
  -1.250   0.4927   0.00916   0.00183  -0.0988   0.5810   0.1889
  -1.000   0.5199   0.00914   0.00185  -0.0987   0.5697   0.2178
  -0.750   0.5467   0.00910   0.00187  -0.0986   0.5580   0.2569
  -0.500   0.5730   0.00898   0.00193  -0.0984   0.5447   0.3402
  -0.250   0.5982   0.00870   0.00201  -0.0982   0.5302   0.4922
   0.000   0.6224   0.00842   0.00211  -0.0976   0.5141   0.6449
   0.250   0.6594   0.00785   0.00225  -0.0992   0.4949   1.0000
   0.500   0.6848   0.00801   0.00232  -0.0988   0.4784   1.0000
   0.750   0.7103   0.00818   0.00239  -0.0983   0.4621   1.0000
   1.000   0.7353   0.00839   0.00248  -0.0978   0.4427   1.0000
   1.250   0.7599   0.00863   0.00259  -0.0973   0.4174   1.0000
   1.500   0.7839   0.00893   0.00272  -0.0966   0.3906   1.0000
   1.750   0.8083   0.00921   0.00287  -0.0961   0.3697   1.0000
   2.000   0.8329   0.00948   0.00304  -0.0956   0.3525   1.0000
   2.250   0.8579   0.00972   0.00320  -0.0952   0.3393   1.0000
   2.500   0.8832   0.00994   0.00336  -0.0948   0.3292   1.0000
   2.750   0.9086   0.01015   0.00353  -0.0945   0.3214   1.0000
   3.000   0.9343   0.01034   0.00369  -0.0942   0.3153   1.0000
   3.250   0.9599   0.01053   0.00387  -0.0939   0.3091   1.0000
   3.750   1.0109   0.01093   0.00424  -0.0934   0.2979   1.0000
   4.000   1.0361   0.01114   0.00445  -0.0931   0.2915   1.0000
   4.250   1.0611   0.01137   0.00466  -0.0927   0.2849   1.0000
   4.500   1.0862   0.01159   0.00487  -0.0924   0.2766   1.0000
   4.750   1.1108   0.01183   0.00509  -0.0920   0.2691   1.0000
   5.000   1.1349   0.01210   0.00534  -0.0916   0.2580   1.0000
   5.250   1.1585   0.01241   0.00559  -0.0910   0.2427   1.0000
   5.500   1.1817   0.01274   0.00586  -0.0905   0.2264   1.0000
   5.750   1.2041   0.01312   0.00617  -0.0898   0.2087   1.0000
   6.000   1.2254   0.01357   0.00653  -0.0890   0.1904   1.0000
   6.250   1.2459   0.01406   0.00693  -0.0880   0.1742   1.0000
   6.500   1.2666   0.01453   0.00735  -0.0871   0.1612   1.0000
   6.750   1.2872   0.01499   0.00778  -0.0862   0.1495   1.0000
   7.000   1.3050   0.01562   0.00831  -0.0848   0.1284   1.0000
   7.250   1.3150   0.01678   0.00915  -0.0824   0.0847   1.0000
   7.500   1.3298   0.01745   0.00978  -0.0805   0.0728   1.0000
   7.750   1.3457   0.01805   0.01037  -0.0788   0.0630   1.0000
   8.250   1.3589   0.02048   0.01252  -0.0730   0.0170   1.0000
   8.500   1.3732   0.02120   0.01329  -0.0713   0.0151   1.0000
   8.750   1.3862   0.02201   0.01416  -0.0695   0.0137   1.0000
   9.000   1.3986   0.02288   0.01510  -0.0677   0.0126   1.0000
   9.250   1.4123   0.02367   0.01596  -0.0662   0.0121   1.0000
   9.500   1.4249   0.02456   0.01694  -0.0646   0.0115   1.0000
   9.750   1.4363   0.02555   0.01801  -0.0630   0.0110   1.0000
  10.000   1.4466   0.02665   0.01919  -0.0614   0.0105   1.0000
  10.250   1.4548   0.02795   0.02057  -0.0597   0.0100   1.0000
  10.500   1.4598   0.02956   0.02228  -0.0579   0.0095   1.0000
  10.750   1.4683   0.03095   0.02375  -0.0566   0.0092   1.0000
  11.000   1.4762   0.03243   0.02533  -0.0554   0.0089   1.0000
  11.250   1.4824   0.03411   0.02711  -0.0542   0.0086   1.0000
  11.500   1.4871   0.03599   0.02908  -0.0531   0.0084   1.0000
  11.750   1.4909   0.03802   0.03120  -0.0520   0.0082   1.0000
  12.000   1.4931   0.04026   0.03354  -0.0511   0.0079   1.0000
  12.250   1.4942   0.04271   0.03609  -0.0503   0.0078   1.0000
  12.500   1.4941   0.04538   0.03886  -0.0497   0.0076   1.0000
  12.750   1.4921   0.04835   0.04194  -0.0493   0.0074   1.0000
  13.000   1.4883   0.05170   0.04540  -0.0491   0.0073   1.0000
  13.250   1.4823   0.05547   0.04929  -0.0492   0.0072   1.0000
  13.500   1.4738   0.05968   0.05363  -0.0495   0.0071   1.0000
  13.750   1.4627   0.06443   0.05851  -0.0501   0.0070   1.0000
  14.000   1.4547   0.06891   0.06310  -0.0509   0.0069   1.0000
  14.250   1.4474   0.07337   0.06769  -0.0517   0.0068   1.0000
  14.500   1.4393   0.07806   0.07250  -0.0528   0.0068   1.0000
  14.750   1.4301   0.08300   0.07757  -0.0540   0.0067   1.0000
  15.000   1.4204   0.08812   0.08281  -0.0554   0.0066   1.0000
  15.250   1.4101   0.09337   0.08817  -0.0568   0.0065   1.0000
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