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NACA 4412 (naca4412-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 4412 (naca4412-il)
Reynolds number: 50,000
Max Cl/Cd: 36.13 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca4412-il-50000-n5.txt
Download as CSV file: xf-naca4412-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 4412                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3702   0.10257   0.09512  -0.0434   1.0000   0.0814
  -9.250  -0.3756   0.09949   0.09212  -0.0434   1.0000   0.0818
  -9.000  -0.3833   0.09645   0.08917  -0.0431   1.0000   0.0820
  -8.750  -0.3944   0.09343   0.08625  -0.0427   1.0000   0.0820
  -8.500  -0.4100   0.09047   0.08341  -0.0417   1.0000   0.0816
  -8.250  -0.4299   0.08732   0.08039  -0.0409   1.0000   0.0810
  -8.000  -0.4479   0.08303   0.07621  -0.0420   1.0000   0.0803
  -7.750  -0.4686   0.07711   0.07032  -0.0448   1.0000   0.0792
  -7.500  -0.4911   0.06887   0.06196  -0.0492   1.0000   0.0780
  -7.250  -0.4987   0.06336   0.05627  -0.0508   1.0000   0.0779
  -7.000  -0.4940   0.06087   0.05373  -0.0500   1.0000   0.0789
  -6.750  -0.4877   0.05850   0.05127  -0.0495   1.0000   0.0805
  -6.500  -0.4810   0.05518   0.04776  -0.0500   1.0000   0.0823
  -6.250  -0.4717   0.05110   0.04334  -0.0512   1.0000   0.0841
  -6.000  -0.4427   0.04575   0.03734  -0.0562   0.9950   0.0860
  -5.750  -0.4092   0.04098   0.03168  -0.0608   0.9891   0.0892
  -5.500  -0.3741   0.03906   0.02956  -0.0638   0.9834   0.0930
  -5.250  -0.3400   0.03717   0.02734  -0.0662   0.9766   0.0971
  -5.000  -0.3028   0.03484   0.02442  -0.0691   0.9709   0.1017
  -4.750  -0.2684   0.03351   0.02292  -0.0712   0.9637   0.1074
  -4.500  -0.2321   0.03231   0.02141  -0.0734   0.9571   0.1148
  -4.250  -0.1973   0.03121   0.02015  -0.0752   0.9496   0.1223
  -4.000  -0.1609   0.03030   0.01893  -0.0771   0.9427   0.1335
  -3.750  -0.1273   0.02962   0.01828  -0.0786   0.9345   0.1451
  -3.500  -0.0919   0.02897   0.01757  -0.0803   0.9272   0.1596
  -3.250  -0.0582   0.02841   0.01695  -0.0816   0.9187   0.1764
  -3.000  -0.0233   0.02793   0.01637  -0.0831   0.9109   0.1972
  -2.750   0.0107   0.02748   0.01598  -0.0844   0.9023   0.2192
  -2.500   0.0446   0.02706   0.01551  -0.0856   0.8938   0.2468
  -2.250   0.0801   0.02658   0.01509  -0.0872   0.8857   0.2797
  -2.000   0.1114   0.02617   0.01480  -0.0880   0.8763   0.3161
  -1.750   0.1483   0.02563   0.01444  -0.0897   0.8691   0.3663
  -1.500   0.1764   0.02515   0.01427  -0.0898   0.8589   0.4272
  -1.250   0.2096   0.02431   0.01404  -0.0903   0.8522   0.5434
  -1.000   0.2272   0.02363   0.01410  -0.0870   0.8414   0.7358
  -0.750   0.2803   0.02308   0.01357  -0.0906   0.8353   1.0000
  -0.500   0.3061   0.02323   0.01348  -0.0904   0.8230   1.0000
  -0.250   0.3355   0.02334   0.01335  -0.0906   0.8126   1.0000
   0.000   0.3708   0.02329   0.01309  -0.0917   0.8045   1.0000
   0.250   0.3965   0.02348   0.01312  -0.0913   0.7926   1.0000
   0.500   0.4283   0.02352   0.01300  -0.0918   0.7836   1.0000
   0.750   0.4582   0.02360   0.01294  -0.0920   0.7736   1.0000
   1.000   0.4847   0.02380   0.01304  -0.0917   0.7624   1.0000
   1.250   0.5198   0.02372   0.01284  -0.0925   0.7549   1.0000
   1.500   0.5435   0.02403   0.01307  -0.0918   0.7427   1.0000
   1.750   0.5716   0.02420   0.01317  -0.0917   0.7328   1.0000
   2.000   0.6027   0.02426   0.01315  -0.0919   0.7237   1.0000
   2.250   0.6269   0.02460   0.01344  -0.0913   0.7123   1.0000
   2.500   0.6593   0.02462   0.01341  -0.0917   0.7042   1.0000
   2.750   0.6835   0.02497   0.01374  -0.0910   0.6928   1.0000
   3.000   0.7090   0.02530   0.01406  -0.0905   0.6824   1.0000
   3.250   0.7403   0.02537   0.01410  -0.0907   0.6739   1.0000
   3.500   0.7624   0.02586   0.01461  -0.0898   0.6624   1.0000
   3.750   0.7907   0.02608   0.01484  -0.0897   0.6532   1.0000
   4.000   0.8168   0.02639   0.01517  -0.0892   0.6430   1.0000
   4.250   0.8399   0.02687   0.01568  -0.0885   0.6322   1.0000
   4.500   0.8722   0.02691   0.01573  -0.0887   0.6241   1.0000
   4.750   0.8917   0.02754   0.01645  -0.0875   0.6123   1.0000
   5.000   0.9163   0.02795   0.01691  -0.0868   0.6020   1.0000
   5.250   0.9455   0.02813   0.01714  -0.0867   0.5927   1.0000
   5.500   0.9652   0.02877   0.01788  -0.0855   0.5810   1.0000
   5.750   0.9905   0.02913   0.01831  -0.0848   0.5707   1.0000
   6.000   1.0175   0.02941   0.01867  -0.0844   0.5605   1.0000
   6.250   1.0364   0.03007   0.01946  -0.0830   0.5485   1.0000
   6.500   1.0604   0.03049   0.01997  -0.0822   0.5375   1.0000
   6.750   1.0886   0.03065   0.02021  -0.0818   0.5267   1.0000
   7.000   1.1063   0.03126   0.02095  -0.0801   0.5130   1.0000
   7.250   1.1256   0.03166   0.02145  -0.0785   0.4982   1.0000
   7.500   1.1446   0.03199   0.02187  -0.0767   0.4824   1.0000
   7.750   1.1625   0.03233   0.02232  -0.0748   0.4661   1.0000
   8.000   1.1790   0.03272   0.02281  -0.0728   0.4495   1.0000
   8.250   1.1940   0.03312   0.02328  -0.0706   0.4319   1.0000
   8.500   1.2081   0.03344   0.02364  -0.0681   0.4129   1.0000
   8.750   1.2133   0.03423   0.02456  -0.0648   0.3924   1.0000
   9.000   1.2172   0.03500   0.02539  -0.0614   0.3714   1.0000
   9.250   1.2229   0.03574   0.02611  -0.0582   0.3496   1.0000
   9.500   1.2242   0.03697   0.02742  -0.0551   0.3266   1.0000
   9.750   1.2270   0.03817   0.02858  -0.0522   0.3030   1.0000
  10.000   1.2268   0.03981   0.03022  -0.0495   0.2781   1.0000
  10.250   1.2259   0.04163   0.03197  -0.0470   0.2536   1.0000
  10.500   1.2235   0.04380   0.03406  -0.0448   0.2301   1.0000
  10.750   1.2203   0.04622   0.03636  -0.0428   0.2093   1.0000
  11.000   1.2168   0.04888   0.03897  -0.0412   0.1904   1.0000
  11.250   1.2134   0.05168   0.04171  -0.0398   0.1746   1.0000
  11.500   1.2106   0.05454   0.04452  -0.0386   0.1616   1.0000
  11.750   1.2084   0.05742   0.04733  -0.0375   0.1507   1.0000
  12.000   1.2078   0.06025   0.05018  -0.0366   0.1408   1.0000
  12.250   1.2092   0.06297   0.05295  -0.0357   0.1324   1.0000
  12.500   1.2115   0.06552   0.05546  -0.0348   0.1256   1.0000
  12.750   1.2154   0.06813   0.05820  -0.0340   0.1188   1.0000
  13.000   1.2196   0.07058   0.06067  -0.0332   0.1129   1.0000
  13.250   1.2253   0.07302   0.06320  -0.0324   0.1078   1.0000
  13.500   1.2306   0.07564   0.06601  -0.0318   0.1031   1.0000
  13.750   1.2392   0.07769   0.06807  -0.0309   0.0988   1.0000
  14.000   1.2432   0.08059   0.07115  -0.0305   0.0950   1.0000
  14.250   1.2420   0.08420   0.07504  -0.0306   0.0916   1.0000
  14.500   1.2438   0.08737   0.07836  -0.0305   0.0885   1.0000
  14.750   1.2590   0.08867   0.07955  -0.0294   0.0849   1.0000
  15.000   1.2455   0.09415   0.08542  -0.0307   0.0832   1.0000
  15.250   1.2309   0.10003   0.09162  -0.0325   0.0815   1.0000
  15.500   1.2146   0.10644   0.09830  -0.0349   0.0800   1.0000
  15.750   1.1958   0.11362   0.10573  -0.0381   0.0788   1.0000
  16.000   1.1706   0.12256   0.11492  -0.0427   0.0781   1.0000
  16.250   1.1230   0.13766   0.13029  -0.0518   0.0786   1.0000
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