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NACA 1412 (naca1412-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 1412 (naca1412-il)
Reynolds number: 100,000
Max Cl/Cd: 43.01 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca1412-il-100000-n5.txt
Download as CSV file: xf-naca1412-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 1412                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.7892   0.08134   0.07563  -0.0333   1.0000   0.0450
 -12.500  -0.8337   0.06943   0.06352  -0.0428   1.0000   0.0444
 -12.250  -0.8670   0.06166   0.05550  -0.0482   1.0000   0.0442
 -12.000  -0.8936   0.05628   0.04984  -0.0501   1.0000   0.0444
 -11.750  -0.9159   0.05228   0.04554  -0.0493   1.0000   0.0447
 -11.500  -0.9339   0.04899   0.04190  -0.0468   1.0000   0.0453
 -11.250  -0.9399   0.04608   0.03868  -0.0449   1.0000   0.0461
 -11.000  -0.9304   0.04435   0.03691  -0.0437   1.0000   0.0471
 -10.750  -0.9220   0.04257   0.03500  -0.0422   1.0000   0.0481
 -10.500  -0.9133   0.04071   0.03296  -0.0407   1.0000   0.0493
 -10.250  -0.9038   0.03888   0.03086  -0.0391   1.0000   0.0508
 -10.000  -0.8933   0.03697   0.02864  -0.0374   1.0000   0.0525
  -9.750  -0.8815   0.03509   0.02638  -0.0357   1.0000   0.0540
  -9.500  -0.8656   0.03344   0.02465  -0.0344   1.0000   0.0553
  -9.250  -0.8488   0.03225   0.02343  -0.0332   1.0000   0.0569
  -8.750  -0.8146   0.02993   0.02083  -0.0304   1.0000   0.0610
  -8.500  -0.7967   0.02870   0.01938  -0.0290   1.0000   0.0629
  -8.250  -0.7784   0.02749   0.01804  -0.0276   1.0000   0.0646
  -8.000  -0.7607   0.02650   0.01709  -0.0262   1.0000   0.0668
  -7.750  -0.7423   0.02565   0.01619  -0.0248   1.0000   0.0696
  -7.500  -0.7235   0.02479   0.01521  -0.0234   1.0000   0.0727
  -7.250  -0.7047   0.02390   0.01423  -0.0219   1.0000   0.0756
  -7.000  -0.6869   0.02304   0.01341  -0.0204   1.0000   0.0787
  -6.750  -0.6683   0.02232   0.01264  -0.0189   1.0000   0.0829
  -6.500  -0.6494   0.02162   0.01189  -0.0174   1.0000   0.0884
  -6.250  -0.6310   0.02094   0.01125  -0.0160   1.0000   0.0947
  -6.000  -0.6119   0.02031   0.01060  -0.0145   1.0000   0.1025
  -5.750  -0.5927   0.01972   0.01001  -0.0132   1.0000   0.1117
  -5.500  -0.5733   0.01915   0.00950  -0.0119   1.0000   0.1232
  -5.250  -0.5533   0.01865   0.00905  -0.0108   1.0000   0.1378
  -5.000  -0.5331   0.01820   0.00865  -0.0096   1.0000   0.1552
  -4.750  -0.5125   0.01778   0.00829  -0.0086   1.0000   0.1758
  -4.500  -0.4918   0.01737   0.00801  -0.0076   1.0000   0.2002
  -4.250  -0.4709   0.01701   0.00777  -0.0067   1.0000   0.2287
  -4.000  -0.4345   0.01662   0.00752  -0.0090   0.9945   0.2691
  -3.750  -0.3982   0.01622   0.00730  -0.0111   0.9879   0.3101
  -3.500  -0.3612   0.01588   0.00711  -0.0133   0.9815   0.3523
  -3.250  -0.3252   0.01555   0.00694  -0.0152   0.9741   0.3964
  -3.000  -0.2904   0.01523   0.00680  -0.0167   0.9663   0.4425
  -2.750  -0.2532   0.01492   0.00669  -0.0187   0.9595   0.4937
  -2.500  -0.2204   0.01464   0.00660  -0.0196   0.9502   0.5441
  -2.250  -0.1822   0.01439   0.00653  -0.0214   0.9439   0.5972
  -2.000  -0.1517   0.01417   0.00648  -0.0216   0.9331   0.6440
  -1.750  -0.1182   0.01399   0.00644  -0.0221   0.9241   0.6895
  -1.500  -0.0849   0.01384   0.00641  -0.0226   0.9143   0.7327
  -1.250  -0.0539   0.01374   0.00641  -0.0225   0.9030   0.7724
  -1.000  -0.0200   0.01366   0.00639  -0.0229   0.8928   0.8095
  -0.750   0.0145   0.01361   0.00637  -0.0234   0.8813   0.8420
  -0.500   0.0494   0.01360   0.00637  -0.0240   0.8682   0.8702
  -0.250   0.0856   0.01359   0.00634  -0.0250   0.8547   0.8954
   0.000   0.1252   0.01357   0.00630  -0.0268   0.8405   0.9161
   0.250   0.1648   0.01355   0.00624  -0.0286   0.8249   0.9347
   0.500   0.2051   0.01354   0.00617  -0.0306   0.8078   0.9511
   0.750   0.2473   0.01351   0.00608  -0.0331   0.7891   0.9651
   1.000   0.2905   0.01347   0.00597  -0.0359   0.7689   0.9775
   1.250   0.3334   0.01344   0.00587  -0.0388   0.7471   0.9890
   1.500   0.3762   0.01342   0.00578  -0.0417   0.7238   0.9997
   1.750   0.3996   0.01344   0.00571  -0.0408   0.7022   1.0000
   2.000   0.4222   0.01350   0.00569  -0.0397   0.6800   1.0000
   2.250   0.4447   0.01359   0.00569  -0.0386   0.6575   1.0000
   2.500   0.4674   0.01370   0.00571  -0.0374   0.6353   1.0000
   2.750   0.4897   0.01384   0.00577  -0.0363   0.6119   1.0000
   3.000   0.5121   0.01400   0.00584  -0.0351   0.5891   1.0000
   3.250   0.5344   0.01419   0.00596  -0.0339   0.5664   1.0000
   3.500   0.5566   0.01439   0.00609  -0.0327   0.5434   1.0000
   3.750   0.5787   0.01463   0.00623  -0.0315   0.5205   1.0000
   4.000   0.6006   0.01487   0.00642  -0.0303   0.4958   1.0000
   4.250   0.6221   0.01514   0.00661  -0.0290   0.4707   1.0000
   4.500   0.6435   0.01543   0.00683  -0.0277   0.4444   1.0000
   4.750   0.6649   0.01575   0.00708  -0.0264   0.4182   1.0000
   5.000   0.6859   0.01610   0.00734  -0.0251   0.3915   1.0000
   5.250   0.7069   0.01647   0.00765  -0.0238   0.3627   1.0000
   5.500   0.7273   0.01691   0.00798  -0.0225   0.3310   1.0000
   5.750   0.7468   0.01742   0.00833  -0.0211   0.2961   1.0000
   6.000   0.7663   0.01799   0.00874  -0.0197   0.2597   1.0000
   6.250   0.7856   0.01862   0.00923  -0.0184   0.2256   1.0000
   6.500   0.8049   0.01929   0.00976  -0.0171   0.1957   1.0000
   6.750   0.8239   0.02000   0.01035  -0.0159   0.1704   1.0000
   7.000   0.8431   0.02073   0.01100  -0.0146   0.1482   1.0000
   7.250   0.8617   0.02153   0.01173  -0.0133   0.1299   1.0000
   7.500   0.8798   0.02237   0.01250  -0.0120   0.1147   1.0000
   7.750   0.8979   0.02321   0.01332  -0.0106   0.1023   1.0000
   8.000   0.9157   0.02407   0.01421  -0.0092   0.0932   1.0000
   8.250   0.9317   0.02508   0.01516  -0.0077   0.0868   1.0000
   8.500   0.9492   0.02599   0.01618  -0.0062   0.0810   1.0000
   8.750   0.9648   0.02701   0.01719  -0.0047   0.0765   1.0000
   9.000   0.9812   0.02804   0.01828  -0.0032   0.0725   1.0000
   9.250   0.9976   0.02904   0.01937  -0.0018   0.0689   1.0000
   9.500   1.0130   0.03014   0.02051  -0.0003   0.0664   1.0000
   9.750   1.0275   0.03144   0.02177   0.0012   0.0644   1.0000
  10.000   1.0443   0.03262   0.02313   0.0025   0.0623   1.0000
  10.250   1.0600   0.03385   0.02450   0.0039   0.0600   1.0000
  10.500   1.0743   0.03508   0.02582   0.0053   0.0579   1.0000
  10.750   1.0871   0.03634   0.02714   0.0069   0.0562   1.0000
  11.000   1.1011   0.03785   0.02865   0.0082   0.0548   1.0000
  11.250   1.1134   0.03949   0.03048   0.0097   0.0536   1.0000
  11.500   1.1226   0.04117   0.03241   0.0114   0.0521   1.0000
  11.750   1.1300   0.04290   0.03435   0.0131   0.0506   1.0000
  12.000   1.1362   0.04467   0.03629   0.0147   0.0493   1.0000
  12.250   1.1419   0.04653   0.03829   0.0162   0.0482   1.0000
  12.500   1.1475   0.04846   0.04032   0.0174   0.0472   1.0000
  12.750   1.1542   0.05051   0.04240   0.0184   0.0463   1.0000
  13.000   1.1515   0.05326   0.04538   0.0195   0.0455   1.0000
  13.250   1.1423   0.05653   0.04898   0.0203   0.0447   1.0000
  13.500   1.1310   0.06025   0.05299   0.0204   0.0441   1.0000
  13.750   1.1176   0.06447   0.05750   0.0198   0.0435   1.0000
  14.000   1.1015   0.06936   0.06265   0.0184   0.0430   1.0000
  14.250   1.0813   0.07516   0.06871   0.0160   0.0427   1.0000
  14.500   1.0555   0.08236   0.07616   0.0122   0.0426   1.0000
  14.750   1.0196   0.09202   0.08609   0.0062   0.0429   1.0000
  15.000   0.9602   0.10790   0.10227  -0.0044   0.0437   1.0000
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