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NACA 63-412 AIRFOIL (n63412-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 63-412 AIRFOIL (n63412-il)
Reynolds number: 100,000
Max Cl/Cd: 56.64 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n63412-il-100000.txt
Download as CSV file: xf-n63412-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63-412 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4645   0.09508   0.09024  -0.0421   1.0000   0.1434
  -9.250  -0.4258   0.09255   0.08760  -0.0366   1.0000   0.1486
  -9.000  -0.4586   0.08890   0.08412  -0.0421   1.0000   0.1568
  -8.750  -0.4385   0.08534   0.08055  -0.0393   1.0000   0.1611
  -8.500  -0.4366   0.08262   0.07788  -0.0390   1.0000   0.1683
  -8.250  -0.5188   0.07808   0.07362  -0.0468   1.0000   0.1722
  -8.000  -0.4524   0.07664   0.07211  -0.0383   1.0000   0.1827
  -7.750  -0.5190   0.07267   0.06836  -0.0423   1.0000   0.1865
  -7.500  -0.4863   0.07128   0.06703  -0.0359   1.0000   0.1947
  -6.750  -0.5919   0.04422   0.03794  -0.0449   1.0000   0.0835
  -6.500  -0.5809   0.04042   0.03396  -0.0440   1.0000   0.0803
  -6.250  -0.5672   0.03727   0.03041  -0.0434   1.0000   0.0793
  -6.000  -0.5501   0.03439   0.02709  -0.0428   1.0000   0.0783
  -5.750  -0.5300   0.03160   0.02377  -0.0423   1.0000   0.0765
  -5.500  -0.5084   0.02948   0.02124  -0.0417   1.0000   0.0764
  -5.250  -0.4687   0.02769   0.01912  -0.0445   0.9951   0.0801
  -5.000  -0.4289   0.02617   0.01719  -0.0468   0.9893   0.0838
  -4.750  -0.3894   0.02434   0.01526  -0.0492   0.9844   0.0875
  -4.500  -0.3531   0.02332   0.01423  -0.0512   0.9780   0.0959
  -4.250  -0.3148   0.02209   0.01310  -0.0534   0.9724   0.1048
  -4.000  -0.2796   0.02114   0.01225  -0.0553   0.9658   0.1207
  -3.750  -0.2422   0.01996   0.01128  -0.0577   0.9594   0.1573
  -3.500  -0.2109   0.01769   0.01123  -0.0594   0.9543   0.5682
  -3.250  -0.1834   0.01819   0.01177  -0.0584   0.9453   0.6331
  -3.000  -0.1516   0.01877   0.01229  -0.0582   0.9379   0.6752
  -2.750  -0.1258   0.01933   0.01286  -0.0566   0.9292   0.7085
  -2.500  -0.1030   0.01994   0.01348  -0.0540   0.9211   0.7399
  -2.250  -0.0788   0.02040   0.01390  -0.0518   0.9132   0.7683
  -2.000  -0.0585   0.02071   0.01418  -0.0492   0.9047   0.7889
  -1.750  -0.0282   0.02079   0.01419  -0.0490   0.8978   0.8063
  -1.500  -0.0028   0.02084   0.01414  -0.0484   0.8897   0.8205
  -1.250   0.0294   0.02079   0.01401  -0.0490   0.8829   0.8342
  -1.000   0.0574   0.02076   0.01391  -0.0490   0.8753   0.8474
  -0.750   0.0864   0.02069   0.01377  -0.0491   0.8679   0.8606
  -0.500   0.1149   0.02062   0.01364  -0.0491   0.8608   0.8741
  -0.250   0.1406   0.02054   0.01352  -0.0487   0.8527   0.8878
   0.000   0.1715   0.02042   0.01335  -0.0491   0.8466   0.9015
   0.250   0.1953   0.02038   0.01329  -0.0485   0.8378   0.9162
   0.500   0.2383   0.02011   0.01299  -0.0508   0.8339   0.9288
   0.750   0.2647   0.02023   0.01312  -0.0512   0.8237   0.9449
   1.000   0.3188   0.01999   0.01286  -0.0559   0.8198   0.9557
   1.250   0.3655   0.02010   0.01299  -0.0602   0.8116   0.9680
   1.500   0.4240   0.01990   0.01280  -0.0662   0.8064   0.9769
   1.750   0.4820   0.01969   0.01262  -0.0720   0.8013   0.9859
   2.000   0.5319   0.01974   0.01272  -0.0772   0.7925   0.9989
   2.250   0.5439   0.01996   0.01295  -0.0752   0.7833   1.0000
   2.500   0.5566   0.02010   0.01310  -0.0731   0.7746   1.0000
   2.750   0.5649   0.02058   0.01362  -0.0708   0.7637   1.0000
   3.000   0.5983   0.02044   0.01349  -0.0716   0.7579   1.0000
   3.250   0.6188   0.02093   0.01403  -0.0713   0.7467   1.0000
   3.500   0.6514   0.02092   0.01405  -0.0720   0.7395   1.0000
   3.750   0.6796   0.02109   0.01430  -0.0722   0.7296   1.0000
   4.000   0.7066   0.02131   0.01459  -0.0722   0.7189   1.0000
   4.250   0.7443   0.02079   0.01412  -0.0728   0.7114   1.0000
   4.500   0.7712   0.02080   0.01422  -0.0723   0.6983   1.0000
   4.750   0.8004   0.02054   0.01403  -0.0718   0.6845   1.0000
   5.000   0.8311   0.02002   0.01358  -0.0711   0.6693   1.0000
   5.250   0.8632   0.01923   0.01282  -0.0703   0.6518   1.0000
   5.500   0.8893   0.01864   0.01228  -0.0687   0.6278   1.0000
   5.750   0.9169   0.01797   0.01160  -0.0673   0.6019   1.0000
   6.000   0.9420   0.01758   0.01125  -0.0658   0.5737   1.0000
   6.250   0.9639   0.01740   0.01114  -0.0641   0.5387   1.0000
   6.500   0.9833   0.01736   0.01106  -0.0619   0.4889   1.0000
   6.750   0.9923   0.01791   0.01113  -0.0582   0.3732   1.0000
   7.000   0.9792   0.02086   0.01259  -0.0527   0.1912   1.0000
   7.250   0.9772   0.02342   0.01448  -0.0490   0.1325   1.0000
   7.500   0.9860   0.02514   0.01604  -0.0465   0.1096   1.0000
   7.750   0.9983   0.02674   0.01752  -0.0445   0.0960   1.0000
   8.000   1.0160   0.02846   0.01916  -0.0432   0.0867   1.0000
   8.250   1.0403   0.03050   0.02098  -0.0429   0.0784   1.0000
   8.500   1.0656   0.03205   0.02272  -0.0425   0.0725   1.0000
   8.750   1.0980   0.03436   0.02493  -0.0432   0.0681   1.0000
   9.000   1.1293   0.03714   0.02788  -0.0436   0.0650   1.0000
   9.250   1.1513   0.03920   0.03026  -0.0428   0.0620   1.0000
   9.500   1.1735   0.04176   0.03310  -0.0422   0.0601   1.0000
   9.750   1.1928   0.04474   0.03643  -0.0412   0.0593   1.0000
  10.000   1.2068   0.04805   0.04015  -0.0397   0.0591   1.0000
  10.250   1.2141   0.05176   0.04432  -0.0377   0.0596   1.0000
  10.500   1.2159   0.05558   0.04859  -0.0353   0.0600   1.0000
  10.750   1.2124   0.05932   0.05273  -0.0328   0.0602   1.0000
  11.000   1.2026   0.06310   0.05686  -0.0300   0.0606   1.0000
  11.250   1.1867   0.06674   0.06080  -0.0270   0.0611   1.0000
  11.500   1.1676   0.07071   0.06504  -0.0246   0.0618   1.0000
  11.750   1.1465   0.07507   0.06963  -0.0233   0.0626   1.0000
  12.000   1.1248   0.07994   0.07471  -0.0229   0.0634   1.0000
  12.250   1.1032   0.08535   0.08030  -0.0236   0.0642   1.0000
  12.500   1.0857   0.09127   0.08634  -0.0250   0.0652   1.0000
  12.750   0.9692   0.09557   0.09108  -0.0209   0.0669   1.0000
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