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N-11 (n11-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: N-11 (n11-il)
Reynolds number: 200,000
Max Cl/Cd: 75.63 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n11-il-200000.txt
Download as CSV file: xf-n11-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3433   0.09315   0.08984  -0.0322   1.0000   0.0605
  -9.250  -0.3594   0.09186   0.08864  -0.0294   1.0000   0.0616
  -9.000  -0.3827   0.09119   0.08807  -0.0254   1.0000   0.0621
  -8.750  -0.3818   0.08303   0.07982  -0.0512   0.9893   0.0656
  -8.500  -0.3702   0.07894   0.07582  -0.0468   0.9875   0.0669
  -8.250  -0.3472   0.07686   0.07373  -0.0456   0.9851   0.0688
  -8.000  -0.3232   0.07308   0.06991  -0.0504   0.9799   0.0717
  -7.750  -0.2883   0.06166   0.05813  -0.0732   0.9709   0.0791
  -7.500  -0.2700   0.05935   0.05589  -0.0724   0.9649   0.0804
  -7.250  -0.2431   0.05695   0.05347  -0.0741   0.9607   0.0830
  -7.000  -0.1579   0.03504   0.03152  -0.0861   0.9429   0.0946
  -6.750  -0.1394   0.03262   0.02906  -0.0864   0.9352   0.0970
  -6.500  -0.1121   0.02688   0.02280  -0.0930   0.9302   0.1077
  -6.250  -0.0796   0.02389   0.01986  -0.0952   0.9282   0.1102
  -6.000  -0.0902   0.02707   0.02100  -0.0966   0.9325   0.0643
  -5.750  -0.0525   0.02399   0.01750  -0.0990   0.9298   0.0625
  -5.500  -0.0122   0.02173   0.01483  -0.1015   0.9278   0.0618
  -5.250   0.0149   0.02052   0.01337  -0.1012   0.9197   0.0627
  -5.000   0.0518   0.01935   0.01196  -0.1027   0.9158   0.0641
  -4.750   0.0907   0.01814   0.01056  -0.1044   0.9129   0.0648
  -4.500   0.1185   0.01736   0.00967  -0.1040   0.9038   0.0656
  -4.250   0.1544   0.01599   0.00830  -0.1052   0.8989   0.0678
  -4.000   0.1828   0.01531   0.00764  -0.1049   0.8898   0.0706
  -3.750   0.2169   0.01466   0.00695  -0.1056   0.8835   0.0757
  -3.500   0.2439   0.01405   0.00636  -0.1051   0.8732   0.0811
  -3.250   0.2748   0.01349   0.00577  -0.1051   0.8650   0.0917
  -3.000   0.3025   0.01268   0.00526  -0.1048   0.8547   0.1476
  -2.750   0.3294   0.01227   0.00505  -0.1044   0.8434   0.2187
  -2.500   0.3570   0.01185   0.00484  -0.1042   0.8332   0.2873
  -2.250   0.3820   0.01117   0.00473  -0.1036   0.8228   0.4537
  -2.000   0.3978   0.01011   0.00484  -0.1003   0.8117   0.8047
  -1.750   0.4619   0.00987   0.00458  -0.1070   0.8032   1.0000
  -1.500   0.4876   0.00993   0.00449  -0.1064   0.7916   1.0000
  -1.250   0.5126   0.01001   0.00444  -0.1056   0.7793   1.0000
  -1.000   0.5381   0.01008   0.00438  -0.1049   0.7674   1.0000
  -0.750   0.5643   0.01014   0.00431  -0.1043   0.7560   1.0000
  -0.500   0.5899   0.01021   0.00426  -0.1037   0.7440   1.0000
  -0.250   0.6151   0.01028   0.00425  -0.1030   0.7311   1.0000
   0.000   0.6406   0.01035   0.00423  -0.1024   0.7183   1.0000
   0.250   0.6663   0.01042   0.00421  -0.1018   0.7052   1.0000
   0.500   0.6920   0.01050   0.00420  -0.1012   0.6916   1.0000
   0.750   0.7177   0.01060   0.00419  -0.1006   0.6778   1.0000
   1.000   0.7433   0.01072   0.00421  -0.1000   0.6633   1.0000
   1.250   0.7685   0.01085   0.00425  -0.0993   0.6475   1.0000
   1.500   0.7933   0.01101   0.00431  -0.0986   0.6301   1.0000
   1.750   0.8178   0.01118   0.00439  -0.0978   0.6116   1.0000
   2.000   0.8421   0.01139   0.00449  -0.0971   0.5927   1.0000
   2.250   0.8662   0.01162   0.00460  -0.0963   0.5735   1.0000
   2.500   0.8900   0.01185   0.00475  -0.0955   0.5531   1.0000
   2.750   0.9136   0.01210   0.00494  -0.0947   0.5329   1.0000
   3.000   0.9370   0.01239   0.00512  -0.0938   0.5130   1.0000
   3.250   0.9603   0.01270   0.00533  -0.0930   0.4932   1.0000
   3.500   0.9835   0.01302   0.00558  -0.0922   0.4739   1.0000
   3.750   1.0068   0.01336   0.00585  -0.0915   0.4564   1.0000
   4.000   1.0299   0.01371   0.00613  -0.0907   0.4401   1.0000
   4.250   1.0529   0.01407   0.00642  -0.0900   0.4247   1.0000
   4.500   1.0758   0.01444   0.00674  -0.0892   0.4100   1.0000
   4.750   1.0986   0.01482   0.00707  -0.0885   0.3966   1.0000
   5.000   1.1216   0.01524   0.00743  -0.0878   0.3852   1.0000
   5.250   1.1448   0.01565   0.00782  -0.0872   0.3749   1.0000
   5.500   1.1682   0.01606   0.00826  -0.0866   0.3650   1.0000
   5.750   1.1914   0.01655   0.00869  -0.0861   0.3559   1.0000
   6.000   1.2139   0.01696   0.00914  -0.0854   0.3458   1.0000
   6.250   1.2359   0.01740   0.00962  -0.0846   0.3352   1.0000
   6.500   1.2565   0.01786   0.01006  -0.0836   0.3232   1.0000
   6.750   1.2760   0.01831   0.01048  -0.0825   0.3103   1.0000
   7.000   1.2955   0.01868   0.01092  -0.0813   0.2985   1.0000
   7.250   1.3154   0.01908   0.01143  -0.0802   0.2879   1.0000
   7.500   1.3340   0.01952   0.01189  -0.0789   0.2770   1.0000
   7.750   1.3511   0.01996   0.01234  -0.0774   0.2651   1.0000
   8.000   1.3687   0.02034   0.01282  -0.0760   0.2531   1.0000
   8.250   1.3854   0.02077   0.01336  -0.0745   0.2414   1.0000
   8.500   1.3994   0.02124   0.01388  -0.0725   0.2287   1.0000
   8.750   1.4121   0.02181   0.01447  -0.0704   0.2134   1.0000
   9.000   1.4238   0.02251   0.01517  -0.0683   0.1977   1.0000
   9.250   1.4328   0.02341   0.01601  -0.0660   0.1805   1.0000
   9.500   1.4416   0.02442   0.01702  -0.0638   0.1633   1.0000
   9.750   1.4477   0.02567   0.01820  -0.0615   0.1393   1.0000
  10.000   1.4490   0.02735   0.01969  -0.0588   0.1016   1.0000
  10.250   1.4416   0.02980   0.02189  -0.0556   0.0766   1.0000
  10.500   1.4380   0.03213   0.02415  -0.0530   0.0545   1.0000
  10.750   1.4347   0.03456   0.02649  -0.0508   0.0409   1.0000
  11.000   1.4328   0.03697   0.02893  -0.0490   0.0360   1.0000
  11.250   1.4314   0.03945   0.03150  -0.0475   0.0335   1.0000
  11.500   1.4269   0.04234   0.03450  -0.0462   0.0318   1.0000
  11.750   1.4220   0.04540   0.03769  -0.0451   0.0307   1.0000
  12.000   1.4181   0.04849   0.04094  -0.0444   0.0298   1.0000
  12.250   1.4128   0.05187   0.04447  -0.0439   0.0291   1.0000
  12.500   1.4064   0.05554   0.04827  -0.0437   0.0284   1.0000
  12.750   1.3990   0.05946   0.05233  -0.0438   0.0278   1.0000
  13.000   1.3909   0.06363   0.05662  -0.0441   0.0273   1.0000
  13.250   1.3820   0.06802   0.06112  -0.0446   0.0268   1.0000
  13.500   1.3723   0.07258   0.06578  -0.0452   0.0263   1.0000
  13.750   1.3625   0.07718   0.07045  -0.0458   0.0258   1.0000
  14.000   1.3541   0.08148   0.07480  -0.0462   0.0254   1.0000
  14.250   1.3514   0.08523   0.07868  -0.0468   0.0249   1.0000
  14.500   1.3490   0.08890   0.08247  -0.0473   0.0245   1.0000
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