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N-11 (n11-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: N-11 (n11-il)
Reynolds number: 1,000,000
Max Cl/Cd: 118.42 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n11-il-1000000.txt
Download as CSV file: xf-n11-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3611   0.09742   0.09579  -0.0390   1.0000   0.0204
 -11.000  -0.3689   0.09380   0.09219  -0.0388   1.0000   0.0205
 -10.750  -0.5031   0.03126   0.02879  -0.1018   0.9842   0.0200
 -10.500  -0.4900   0.02533   0.02218  -0.1053   0.9791   0.0208
 -10.250  -0.4628   0.02392   0.02069  -0.1065   0.9758   0.0213
 -10.000  -0.4324   0.02315   0.01987  -0.1077   0.9732   0.0217
  -9.750  -0.4020   0.02256   0.01924  -0.1087   0.9707   0.0221
  -9.500  -0.3801   0.02163   0.01821  -0.1081   0.9636   0.0225
  -9.250  -0.3551   0.02040   0.01681  -0.1081   0.9582   0.0231
  -9.000  -0.3319   0.01939   0.01562  -0.1076   0.9507   0.0238
  -8.750  -0.3070   0.01849   0.01454  -0.1072   0.9433   0.0244
  -8.500  -0.2823   0.01788   0.01376  -0.1066   0.9336   0.0248
  -8.250  -0.2578   0.01696   0.01260  -0.1062   0.9236   0.0252
  -8.000  -0.2363   0.01469   0.01007  -0.1056   0.9116   0.0259
  -7.750  -0.2108   0.01403   0.00934  -0.1052   0.8984   0.0265
  -7.500  -0.1847   0.01353   0.00873  -0.1048   0.8851   0.0270
  -7.250  -0.1585   0.01297   0.00806  -0.1045   0.8727   0.0274
  -7.000  -0.1322   0.01244   0.00740  -0.1041   0.8610   0.0279
  -6.750  -0.1058   0.01196   0.00679  -0.1037   0.8499   0.0283
  -6.500  -0.0791   0.01152   0.00624  -0.1033   0.8395   0.0288
  -6.250  -0.0521   0.01116   0.00579  -0.1030   0.8305   0.0294
  -6.000  -0.0249   0.01089   0.00542  -0.1027   0.8221   0.0299
  -5.750   0.0025   0.01054   0.00502  -0.1025   0.8149   0.0302
  -5.500   0.0298   0.01025   0.00465  -0.1023   0.8075   0.0304
  -5.250   0.0574   0.01000   0.00435  -0.1021   0.7997   0.0306
  -5.000   0.0837   0.00940   0.00367  -0.1017   0.7919   0.0311
  -4.750   0.1107   0.00894   0.00315  -0.1015   0.7846   0.0318
  -4.500   0.1380   0.00865   0.00282  -0.1013   0.7766   0.0325
  -4.250   0.1657   0.00844   0.00258  -0.1012   0.7684   0.0335
  -4.000   0.1932   0.00828   0.00237  -0.1009   0.7589   0.0344
  -3.750   0.2210   0.00812   0.00217  -0.1008   0.7484   0.0351
  -3.500   0.2487   0.00799   0.00200  -0.1007   0.7382   0.0359
  -3.250   0.2764   0.00790   0.00184  -0.1005   0.7272   0.0367
  -3.000   0.3042   0.00781   0.00171  -0.1004   0.7150   0.0373
  -2.750   0.3319   0.00769   0.00155  -0.1002   0.7018   0.0397
  -2.500   0.3593   0.00762   0.00144  -0.1000   0.6875   0.0432
  -2.250   0.3864   0.00749   0.00136  -0.0998   0.6723   0.0703
  -2.000   0.4132   0.00734   0.00132  -0.0996   0.6566   0.1227
  -1.750   0.4401   0.00726   0.00132  -0.0995   0.6413   0.1687
  -1.500   0.4673   0.00722   0.00133  -0.0993   0.6273   0.2054
  -1.250   0.4943   0.00718   0.00134  -0.0992   0.6126   0.2469
  -1.000   0.5207   0.00702   0.00137  -0.0990   0.5972   0.3387
  -0.750   0.5465   0.00674   0.00143  -0.0989   0.5829   0.4859
  -0.500   0.5714   0.00637   0.00151  -0.0984   0.5709   0.6642
  -0.250   0.5915   0.00578   0.00165  -0.0963   0.5593   0.9556
   0.000   0.6409   0.00590   0.00168  -0.1012   0.5428   1.0000
   0.250   0.6665   0.00603   0.00172  -0.1007   0.5279   1.0000
   0.500   0.6924   0.00614   0.00177  -0.1003   0.5142   1.0000
   0.750   0.7182   0.00628   0.00183  -0.0999   0.4992   1.0000
   1.000   0.7435   0.00646   0.00190  -0.0994   0.4802   1.0000
   1.250   0.7689   0.00664   0.00198  -0.0990   0.4566   1.0000
   1.500   0.7936   0.00689   0.00208  -0.0985   0.4284   1.0000
   1.750   0.8180   0.00718   0.00221  -0.0979   0.3979   1.0000
   2.000   0.8429   0.00744   0.00235  -0.0974   0.3751   1.0000
   2.250   0.8682   0.00768   0.00249  -0.0970   0.3589   1.0000
   2.500   0.8940   0.00787   0.00262  -0.0967   0.3467   1.0000
   2.750   0.9199   0.00807   0.00277  -0.0965   0.3361   1.0000
   3.000   0.9455   0.00828   0.00292  -0.0962   0.3263   1.0000
   3.250   0.9720   0.00843   0.00305  -0.0960   0.3196   1.0000
   3.500   0.9976   0.00863   0.00322  -0.0958   0.3121   1.0000
   3.750   1.0241   0.00878   0.00335  -0.0957   0.3059   1.0000
   4.000   1.0498   0.00898   0.00352  -0.0954   0.2985   1.0000
   4.250   1.0759   0.00915   0.00368  -0.0953   0.2904   1.0000
   4.500   1.1012   0.00937   0.00385  -0.0950   0.2818   1.0000
   4.750   1.1274   0.00952   0.00401  -0.0949   0.2751   1.0000
   5.000   1.1524   0.00976   0.00420  -0.0945   0.2646   1.0000
   5.250   1.1778   0.00996   0.00438  -0.0943   0.2544   1.0000
   5.500   1.2028   0.01020   0.00458  -0.0940   0.2432   1.0000
   5.750   1.2269   0.01049   0.00481  -0.0936   0.2281   1.0000
   6.000   1.2494   0.01090   0.00510  -0.0929   0.2067   1.0000
   6.250   1.2709   0.01137   0.00545  -0.0921   0.1842   1.0000
   6.500   1.2924   0.01184   0.00582  -0.0913   0.1677   1.0000
   6.750   1.3140   0.01227   0.00619  -0.0905   0.1537   1.0000
   7.000   1.3349   0.01276   0.00659  -0.0896   0.1375   1.0000
   7.250   1.3486   0.01374   0.00728  -0.0877   0.0925   1.0000
   7.500   1.3648   0.01452   0.00793  -0.0860   0.0726   1.0000
   7.750   1.3789   0.01541   0.00866  -0.0841   0.0484   1.0000
   8.000   1.3845   0.01673   0.00977  -0.0807   0.0183   1.0000
   8.250   1.4004   0.01730   0.01037  -0.0789   0.0161   1.0000
   8.500   1.4166   0.01785   0.01097  -0.0773   0.0152   1.0000
   8.750   1.4310   0.01852   0.01168  -0.0754   0.0142   1.0000
   9.000   1.4431   0.01934   0.01256  -0.0733   0.0131   1.0000
   9.250   1.4585   0.01994   0.01322  -0.0717   0.0127   1.0000
   9.500   1.4726   0.02065   0.01398  -0.0700   0.0123   1.0000
   9.750   1.4853   0.02145   0.01484  -0.0683   0.0118   1.0000
  10.000   1.4969   0.02233   0.01578  -0.0664   0.0114   1.0000
  10.250   1.5066   0.02338   0.01688  -0.0645   0.0110   1.0000
  10.500   1.5125   0.02473   0.01832  -0.0622   0.0106   1.0000
  10.750   1.5144   0.02643   0.02014  -0.0598   0.0102   1.0000
  11.000   1.5248   0.02757   0.02134  -0.0584   0.0101   1.0000
  11.250   1.5330   0.02892   0.02276  -0.0570   0.0099   1.0000
  11.500   1.5404   0.03040   0.02431  -0.0557   0.0097   1.0000
  11.750   1.5465   0.03204   0.02603  -0.0544   0.0094   1.0000
  12.000   1.5518   0.03381   0.02788  -0.0532   0.0092   1.0000
  12.250   1.5561   0.03574   0.02989  -0.0522   0.0089   1.0000
  12.500   1.5587   0.03789   0.03212  -0.0512   0.0087   1.0000
  12.750   1.5594   0.04031   0.03462  -0.0504   0.0086   1.0000
  13.000   1.5575   0.04311   0.03751  -0.0496   0.0084   1.0000
  13.250   1.5527   0.04637   0.04086  -0.0491   0.0083   1.0000
  13.500   1.5442   0.05021   0.04482  -0.0488   0.0081   1.0000
  13.750   1.5318   0.05475   0.04948  -0.0488   0.0080   1.0000
  14.000   1.5161   0.05989   0.05475  -0.0492   0.0079   1.0000
  14.250   1.5021   0.06500   0.05999  -0.0498   0.0078   1.0000
  14.500   1.4983   0.06890   0.06398  -0.0505   0.0078   1.0000
  14.750   1.4924   0.07314   0.06833  -0.0513   0.0077   1.0000
  15.000   1.4860   0.07750   0.07279  -0.0522   0.0077   1.0000
  15.250   1.4778   0.08223   0.07762  -0.0534   0.0076   1.0000
  15.500   1.4688   0.08714   0.08264  -0.0546   0.0076   1.0000
  15.750   1.4595   0.09215   0.08774  -0.0560   0.0075   1.0000
  16.000   1.4503   0.09721   0.09290  -0.0574   0.0074   1.0000
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