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N-12 (n12-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: N-12 (n12-il)
Reynolds number: 50,000
Max Cl/Cd: 27.66 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n12-il-50000-n5.txt
Download as CSV file: xf-n12-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: N-12                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.6760   0.09257   0.08496  -0.0258   1.0000   0.0597
 -11.000  -0.7001   0.08388   0.07632  -0.0316   1.0000   0.0590
 -10.750  -0.7270   0.07679   0.06918  -0.0358   1.0000   0.0582
 -10.500  -0.7546   0.07116   0.06346  -0.0375   1.0000   0.0575
 -10.250  -0.7803   0.06678   0.05894  -0.0365   1.0000   0.0573
 -10.000  -0.8023   0.06315   0.05514  -0.0339   1.0000   0.0572
  -9.750  -0.8178   0.05943   0.05117  -0.0313   1.0000   0.0572
  -9.500  -0.8278   0.05582   0.04725  -0.0286   1.0000   0.0573
  -9.250  -0.8325   0.05238   0.04346  -0.0259   1.0000   0.0576
  -9.000  -0.8322   0.04924   0.03996  -0.0233   1.0000   0.0584
  -8.750  -0.8285   0.04633   0.03664  -0.0207   1.0000   0.0599
  -8.500  -0.8215   0.04356   0.03338  -0.0183   1.0000   0.0617
  -8.250  -0.8092   0.04095   0.03035  -0.0163   1.0000   0.0630
  -8.000  -0.7919   0.03873   0.02799  -0.0149   1.0000   0.0643
  -7.750  -0.7736   0.03681   0.02590  -0.0136   1.0000   0.0657
  -7.500  -0.7552   0.03520   0.02414  -0.0121   1.0000   0.0683
  -7.250  -0.7356   0.03367   0.02237  -0.0108   1.0000   0.0717
  -7.000  -0.7142   0.03215   0.02066  -0.0095   1.0000   0.0743
  -6.750  -0.6947   0.03086   0.01931  -0.0081   1.0000   0.0766
  -6.500  -0.6751   0.02969   0.01805  -0.0066   1.0000   0.0795
  -6.250  -0.6559   0.02858   0.01680  -0.0050   1.0000   0.0830
  -6.000  -0.6377   0.02757   0.01571  -0.0033   1.0000   0.0875
  -5.750  -0.6197   0.02665   0.01473  -0.0016   1.0000   0.0963
  -5.500  -0.6024   0.02567   0.01373   0.0002   1.0000   0.1078
  -5.250  -0.5851   0.02462   0.01270   0.0019   1.0000   0.1247
  -5.000  -0.5682   0.02354   0.01172   0.0037   1.0000   0.1527
  -4.750  -0.5519   0.02246   0.01089   0.0054   1.0000   0.1975
  -4.500  -0.5379   0.02137   0.01030   0.0074   1.0000   0.2696
  -4.250  -0.5222   0.02068   0.00988   0.0095   1.0000   0.3446
  -4.000  -0.5057   0.02014   0.00945   0.0116   1.0000   0.4062
  -3.750  -0.4918   0.01951   0.00917   0.0143   1.0000   0.4725
  -3.500  -0.4757   0.01903   0.00899   0.0169   1.0000   0.5341
  -3.250  -0.4572   0.01870   0.00898   0.0194   1.0000   0.6055
  -3.000  -0.4355   0.01856   0.00910   0.0216   1.0000   0.6841
  -2.750  -0.4052   0.01873   0.00943   0.0228   1.0000   0.7604
  -2.500  -0.3695   0.01916   0.00987   0.0230   1.0000   0.8286
  -2.250  -0.3223   0.01965   0.01023   0.0207   1.0000   0.8761
  -2.000  -0.2672   0.02000   0.01035   0.0162   1.0000   0.9055
  -1.750  -0.2146   0.02013   0.01028   0.0115   1.0000   0.9233
  -1.500  -0.1684   0.02014   0.01012   0.0076   1.0000   0.9402
  -1.250  -0.1250   0.02010   0.00996   0.0040   1.0000   0.9570
  -1.000  -0.0825   0.02005   0.00981   0.0004   1.0000   0.9741
  -0.750  -0.0364   0.01990   0.00960  -0.0040   1.0000   0.9887
  -0.500   0.0021   0.01978   0.00942  -0.0073   1.0000   1.0000
  -0.250   0.0048   0.01972   0.00938  -0.0039   1.0000   1.0000
   0.000   0.0061   0.01973   0.00939  -0.0002   1.0000   1.0000
   0.250   0.0069   0.01980   0.00946   0.0035   1.0000   1.0000
   0.500   0.0258   0.01991   0.00959   0.0038   0.9946   1.0000
   0.750   0.0942   0.01985   0.00958  -0.0047   0.9678   1.0000
   1.000   0.1473   0.01970   0.00950  -0.0099   0.9425   1.0000
   1.250   0.1971   0.01954   0.00943  -0.0144   0.9224   1.0000
   1.500   0.2460   0.01937   0.00938  -0.0185   0.9017   1.0000
   1.750   0.2942   0.01919   0.00932  -0.0223   0.8784   1.0000
   2.000   0.3361   0.01904   0.00928  -0.0248   0.8504   1.0000
   2.250   0.3733   0.01893   0.00928  -0.0262   0.8188   1.0000
   2.500   0.4065   0.01883   0.00924  -0.0266   0.7821   1.0000
   2.750   0.4341   0.01880   0.00925  -0.0259   0.7403   1.0000
   3.000   0.4590   0.01883   0.00926  -0.0246   0.6960   1.0000
   3.250   0.4820   0.01894   0.00928  -0.0229   0.6490   1.0000
   3.500   0.5026   0.01917   0.00941  -0.0209   0.6036   1.0000
   3.750   0.5218   0.01947   0.00963  -0.0188   0.5615   1.0000
   4.000   0.5408   0.01983   0.00994  -0.0168   0.5251   1.0000
   4.250   0.5583   0.02024   0.01025  -0.0146   0.4829   1.0000
   4.500   0.5728   0.02071   0.01052  -0.0119   0.4309   1.0000
   4.750   0.5851   0.02131   0.01077  -0.0089   0.3703   1.0000
   5.000   0.5973   0.02204   0.01117  -0.0063   0.3094   1.0000
   5.250   0.6121   0.02276   0.01175  -0.0041   0.2552   1.0000
   5.500   0.6269   0.02361   0.01247  -0.0019   0.1876   1.0000
   5.750   0.6397   0.02491   0.01328   0.0003   0.1380   1.0000
   6.000   0.6529   0.02638   0.01451   0.0025   0.1204   1.0000
   6.250   0.6678   0.02774   0.01584   0.0045   0.1081   1.0000
   6.500   0.6844   0.02899   0.01718   0.0064   0.0984   1.0000
   6.750   0.7012   0.03036   0.01852   0.0081   0.0924   1.0000
   7.000   0.7219   0.03165   0.02005   0.0096   0.0877   1.0000
   7.250   0.7427   0.03307   0.02163   0.0110   0.0836   1.0000
   7.500   0.7621   0.03463   0.02316   0.0122   0.0795   1.0000
   7.750   0.7805   0.03615   0.02503   0.0138   0.0749   1.0000
   8.000   0.7986   0.03789   0.02700   0.0153   0.0717   1.0000
   8.250   0.8162   0.03983   0.02914   0.0167   0.0694   1.0000
   8.500   0.8321   0.04197   0.03136   0.0181   0.0669   1.0000
   8.750   0.8407   0.04432   0.03423   0.0206   0.0643   1.0000
   9.000   0.8479   0.04673   0.03702   0.0230   0.0619   1.0000
   9.250   0.8533   0.04946   0.04007   0.0253   0.0605   1.0000
   9.500   0.8560   0.05227   0.04318   0.0277   0.0592   1.0000
   9.750   0.8576   0.05495   0.04608   0.0300   0.0580   1.0000
  10.000   0.8612   0.05745   0.04865   0.0318   0.0563   1.0000
  10.250   0.8539   0.06065   0.05204   0.0342   0.0554   1.0000
  10.500   0.8353   0.06399   0.05567   0.0372   0.0550   1.0000
  10.750   0.8133   0.06741   0.05928   0.0398   0.0549   1.0000
  11.000   0.7908   0.07142   0.06346   0.0405   0.0549   1.0000
  11.250   0.7697   0.07610   0.06826   0.0395   0.0551   1.0000
  11.500   0.7473   0.08187   0.07411   0.0368   0.0553   1.0000
  11.750   0.7263   0.08850   0.08079   0.0329   0.0556   1.0000
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