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N-14 (n14-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: N-14 (n14-il)
Reynolds number: 100,000
Max Cl/Cd: 36.78 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n14-il-100000-n5.txt
Download as CSV file: xf-n14-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: N-14                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.7819   0.08136   0.07560  -0.0426   1.0000   0.0419
 -13.000  -0.8500   0.06752   0.06142  -0.0518   1.0000   0.0404
 -12.750  -0.8784   0.06183   0.05551  -0.0535   1.0000   0.0404
 -12.500  -0.9007   0.05750   0.05095  -0.0534   1.0000   0.0405
 -12.250  -0.9170   0.05420   0.04745  -0.0521   1.0000   0.0409
 -12.000  -0.9309   0.05135   0.04440  -0.0499   1.0000   0.0415
 -11.750  -0.9429   0.04880   0.04162  -0.0470   1.0000   0.0421
 -11.500  -0.9531   0.04650   0.03909  -0.0435   1.0000   0.0427
 -11.250  -0.9613   0.04448   0.03681  -0.0395   1.0000   0.0434
 -11.000  -0.9667   0.04253   0.03458  -0.0356   1.0000   0.0445
 -10.750  -0.9676   0.04066   0.03235  -0.0320   1.0000   0.0455
 -10.500  -0.9632   0.03870   0.03016  -0.0293   1.0000   0.0466
 -10.250  -0.9531   0.03693   0.02833  -0.0272   1.0000   0.0479
 -10.000  -0.9425   0.03550   0.02681  -0.0250   1.0000   0.0491
  -9.750  -0.9314   0.03419   0.02538  -0.0228   1.0000   0.0508
  -9.500  -0.9192   0.03291   0.02393  -0.0206   1.0000   0.0526
  -9.250  -0.9053   0.03156   0.02237  -0.0185   1.0000   0.0542
  -9.000  -0.8900   0.03026   0.02085  -0.0166   1.0000   0.0555
  -8.750  -0.8746   0.02899   0.01949  -0.0148   1.0000   0.0569
  -8.500  -0.8610   0.02795   0.01846  -0.0127   1.0000   0.0588
  -8.250  -0.8470   0.02710   0.01758  -0.0105   1.0000   0.0610
  -8.000  -0.8323   0.02623   0.01664  -0.0083   1.0000   0.0633
  -7.750  -0.8176   0.02537   0.01566  -0.0061   1.0000   0.0654
  -7.500  -0.8038   0.02454   0.01480  -0.0037   1.0000   0.0675
  -7.250  -0.7903   0.02386   0.01414  -0.0013   1.0000   0.0700
  -7.000  -0.7760   0.02326   0.01351   0.0010   1.0000   0.0735
  -6.750  -0.7615   0.02269   0.01292   0.0033   1.0000   0.0785
  -6.500  -0.7468   0.02218   0.01238   0.0056   1.0000   0.0850
  -6.250  -0.7325   0.02163   0.01179   0.0080   1.0000   0.0931
  -6.000  -0.7179   0.02110   0.01119   0.0103   1.0000   0.1032
  -5.750  -0.7041   0.02055   0.01061   0.0128   1.0000   0.1142
  -5.500  -0.6906   0.02000   0.01008   0.0152   1.0000   0.1245
  -5.250  -0.6761   0.01955   0.00961   0.0174   1.0000   0.1355
  -5.000  -0.6613   0.01912   0.00922   0.0196   1.0000   0.1478
  -4.750  -0.6465   0.01872   0.00889   0.0218   1.0000   0.1626
  -4.500  -0.6311   0.01835   0.00860   0.0238   1.0000   0.1794
  -4.250  -0.6134   0.01797   0.00833   0.0254   0.9994   0.2053
  -4.000  -0.5827   0.01752   0.00812   0.0242   0.9946   0.2517
  -3.750  -0.5541   0.01701   0.00789   0.0234   0.9894   0.3064
  -3.500  -0.5247   0.01654   0.00769   0.0226   0.9845   0.3670
  -3.250  -0.4981   0.01608   0.00750   0.0225   0.9788   0.4251
  -3.000  -0.4687   0.01570   0.00741   0.0220   0.9739   0.4901
  -2.750  -0.4421   0.01536   0.00736   0.0222   0.9681   0.5602
  -2.500  -0.4112   0.01518   0.00744   0.0218   0.9632   0.6300
  -2.250  -0.3752   0.01515   0.00763   0.0206   0.9598   0.6962
  -2.000  -0.3448   0.01519   0.00777   0.0205   0.9539   0.7460
  -1.750  -0.3083   0.01531   0.00793   0.0191   0.9496   0.7842
  -1.500  -0.2674   0.01546   0.00807   0.0168   0.9464   0.8120
  -1.250  -0.2359   0.01558   0.00819   0.0164   0.9396   0.8365
  -1.000  -0.1909   0.01573   0.00831   0.0133   0.9346   0.8549
  -0.750  -0.1461   0.01579   0.00834   0.0103   0.9278   0.8695
  -0.500  -0.1009   0.01581   0.00833   0.0073   0.9193   0.8836
  -0.250  -0.0457   0.01588   0.00839   0.0026   0.9119   0.8958
   0.000   0.0128   0.01600   0.00852  -0.0027   0.9038   0.9084
   0.250   0.0728   0.01618   0.00871  -0.0084   0.8981   0.9210
   0.500   0.1174   0.01625   0.00881  -0.0113   0.8891   0.9323
   0.750   0.1666   0.01616   0.00874  -0.0154   0.8802   0.9370
   1.000   0.2088   0.01601   0.00862  -0.0182   0.8694   0.9423
   1.250   0.2465   0.01588   0.00852  -0.0200   0.8555   0.9476
   1.500   0.2892   0.01570   0.00839  -0.0228   0.8398   0.9511
   1.750   0.3280   0.01552   0.00822  -0.0247   0.8176   0.9556
   2.000   0.3619   0.01537   0.00805  -0.0254   0.7865   0.9608
   2.250   0.3983   0.01520   0.00782  -0.0266   0.7414   0.9646
   2.500   0.4303   0.01514   0.00769  -0.0271   0.6919   0.9699
   2.750   0.4626   0.01515   0.00753  -0.0276   0.6344   0.9745
   3.000   0.4938   0.01532   0.00739  -0.0281   0.5603   0.9789
   3.250   0.5199   0.01572   0.00740  -0.0277   0.4806   0.9845
   3.500   0.5483   0.01616   0.00746  -0.0282   0.4121   0.9892
   3.750   0.5769   0.01656   0.00764  -0.0287   0.3657   0.9943
   4.000   0.6074   0.01691   0.00782  -0.0297   0.3244   0.9990
   4.250   0.6267   0.01724   0.00805  -0.0284   0.2913   1.0000
   4.500   0.6427   0.01756   0.00828  -0.0264   0.2594   1.0000
   4.750   0.6583   0.01790   0.00854  -0.0243   0.2261   1.0000
   5.000   0.6731   0.01832   0.00882  -0.0222   0.1933   1.0000
   5.250   0.6873   0.01883   0.00917  -0.0199   0.1647   1.0000
   5.500   0.7013   0.01938   0.00961  -0.0176   0.1419   1.0000
   5.750   0.7152   0.01995   0.01013  -0.0152   0.1239   1.0000
   6.000   0.7288   0.02055   0.01070  -0.0127   0.1105   1.0000
   6.250   0.7418   0.02120   0.01128  -0.0102   0.1011   1.0000
   6.500   0.7561   0.02175   0.01189  -0.0078   0.0927   1.0000
   6.750   0.7692   0.02238   0.01250  -0.0052   0.0869   1.0000
   7.000   0.7832   0.02298   0.01319  -0.0028   0.0822   1.0000
   7.250   0.7965   0.02365   0.01388  -0.0003   0.0787   1.0000
   7.500   0.8089   0.02443   0.01463   0.0023   0.0758   1.0000
   7.750   0.8232   0.02517   0.01548   0.0046   0.0728   1.0000
   8.000   0.8373   0.02593   0.01630   0.0069   0.0696   1.0000
   8.250   0.8507   0.02676   0.01714   0.0092   0.0669   1.0000
   8.500   0.8643   0.02789   0.01822   0.0114   0.0647   1.0000
   8.750   0.8799   0.02886   0.01939   0.0134   0.0623   1.0000
   9.000   0.8944   0.02989   0.02056   0.0155   0.0596   1.0000
   9.250   0.9083   0.03096   0.02171   0.0175   0.0571   1.0000
   9.500   0.9217   0.03214   0.02289   0.0195   0.0548   1.0000
   9.750   0.9352   0.03374   0.02460   0.0213   0.0526   1.0000
  10.000   0.9460   0.03506   0.02621   0.0238   0.0506   1.0000
  10.250   0.9550   0.03650   0.02788   0.0264   0.0484   1.0000
  10.500   0.9629   0.03783   0.02935   0.0289   0.0464   1.0000
  10.750   0.9707   0.03917   0.03074   0.0313   0.0447   1.0000
  11.000   0.9798   0.04117   0.03273   0.0332   0.0432   1.0000
  11.250   0.9757   0.04293   0.03486   0.0372   0.0421   1.0000
  11.500   0.9682   0.04481   0.03704   0.0414   0.0410   1.0000
  11.750   0.9603   0.04682   0.03933   0.0451   0.0400   1.0000
  12.000   0.9520   0.04899   0.04172   0.0481   0.0390   1.0000
  12.250   0.9433   0.05127   0.04419   0.0504   0.0381   1.0000
  12.500   0.9347   0.05366   0.04673   0.0522   0.0371   1.0000
  12.750   0.9255   0.05639   0.04959   0.0533   0.0365   1.0000
  13.000   0.9155   0.05942   0.05275   0.0538   0.0360   1.0000
  13.250   0.9011   0.06325   0.05674   0.0535   0.0357   1.0000
  13.500   0.8807   0.06821   0.06189   0.0520   0.0356   1.0000
  13.750   0.8462   0.07595   0.06991   0.0477   0.0358   1.0000
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