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NACA 64(1)-212 MOD B (n64212mb-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 64(1)-212 MOD B (n64212mb-il)
Reynolds number: 100,000
Max Cl/Cd: 30.65 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n64212mb-il-100000.txt
Download as CSV file: xf-n64212mb-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(1)-212 MOD B                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5141   0.09639   0.09141  -0.0184   1.0000   0.1594
  -9.500  -0.4944   0.09395   0.08895  -0.0165   1.0000   0.1648
  -9.250  -0.5931   0.08625   0.08147  -0.0309   1.0000   0.1726
  -9.000  -0.4996   0.08623   0.08135  -0.0193   1.0000   0.1792
  -8.750  -0.5958   0.07913   0.07441  -0.0308   1.0000   0.1885
  -8.500  -0.5063   0.07875   0.07402  -0.0216   1.0000   0.1960
  -8.250  -0.5687   0.07212   0.06753  -0.0283   1.0000   0.2070
  -7.500  -0.6539   0.04349   0.03657  -0.0316   1.0000   0.0854
  -7.250  -0.6437   0.04069   0.03352  -0.0292   1.0000   0.0806
  -7.000  -0.6354   0.03791   0.03051  -0.0268   1.0000   0.0785
  -6.750  -0.6262   0.03564   0.02795  -0.0243   1.0000   0.0779
  -6.500  -0.6150   0.03361   0.02562  -0.0220   1.0000   0.0778
  -6.250  -0.6016   0.03163   0.02335  -0.0198   1.0000   0.0773
  -6.000  -0.5861   0.02976   0.02119  -0.0179   1.0000   0.0767
  -5.750  -0.5691   0.02815   0.01934  -0.0161   1.0000   0.0769
  -5.500  -0.5510   0.02676   0.01777  -0.0145   1.0000   0.0777
  -5.250  -0.5324   0.02559   0.01646  -0.0130   1.0000   0.0795
  -5.000  -0.5134   0.02474   0.01541  -0.0115   1.0000   0.0825
  -4.750  -0.4938   0.02342   0.01413  -0.0103   1.0000   0.0855
  -4.500  -0.4746   0.02245   0.01325  -0.0090   1.0000   0.0889
  -4.250  -0.4554   0.02172   0.01251  -0.0077   1.0000   0.0938
  -4.000  -0.4372   0.02084   0.01173  -0.0064   1.0000   0.1005
  -3.750  -0.4187   0.02019   0.01113  -0.0052   1.0000   0.1099
  -3.500  -0.3950   0.01938   0.01045  -0.0051   0.9984   0.1264
  -3.250  -0.3651   0.01647   0.00922  -0.0076   0.9941   0.3563
  -3.000  -0.3434   0.01664   0.01052  -0.0048   0.9874   0.6531
  -2.750  -0.3135   0.01741   0.01128  -0.0042   0.9811   0.6998
  -2.500  -0.2858   0.01806   0.01192  -0.0032   0.9738   0.7314
  -2.250  -0.2627   0.01895   0.01287  -0.0003   0.9655   0.7677
  -2.000  -0.2406   0.02013   0.01416   0.0044   0.9553   0.8066
  -1.750  -0.2047   0.02062   0.01458   0.0052   0.9416   0.8321
  -1.500  -0.1490   0.02051   0.01434   0.0012   0.9258   0.8402
  -1.250  -0.1074   0.02029   0.01400  -0.0011   0.9122   0.8508
  -1.000  -0.0642   0.02016   0.01380  -0.0031   0.9011   0.8579
  -0.750  -0.0078   0.01984   0.01338  -0.0077   0.8928   0.8655
  -0.500   0.0253   0.01960   0.01311  -0.0080   0.8804   0.8730
  -0.250   0.0614   0.01925   0.01271  -0.0090   0.8685   0.8818
   0.000   0.1072   0.01876   0.01217  -0.0109   0.8567   0.8878
   0.250   0.1422   0.01829   0.01167  -0.0111   0.8426   0.8965
   0.500   0.1758   0.01780   0.01116  -0.0110   0.8265   0.9042
   0.750   0.2061   0.01724   0.01057  -0.0102   0.8083   0.9136
   1.000   0.2397   0.01666   0.00997  -0.0099   0.7830   0.9215
   1.250   0.2697   0.01603   0.00929  -0.0089   0.7532   0.9316
   1.500   0.3046   0.01539   0.00855  -0.0086   0.6986   0.9401
   1.750   0.3326   0.01513   0.00761  -0.0070   0.5257   0.9493
   2.000   0.3579   0.01624   0.00751  -0.0070   0.3782   0.9598
   2.250   0.4005   0.01697   0.00779  -0.0104   0.3448   0.9676
   2.500   0.4437   0.01748   0.00807  -0.0138   0.3255   0.9758
   2.750   0.4865   0.01798   0.00836  -0.0172   0.3123   0.9845
   3.000   0.5319   0.01842   0.00872  -0.0211   0.3016   0.9931
   3.250   0.5717   0.01901   0.00910  -0.0242   0.2932   1.0000
   3.500   0.5872   0.01928   0.00945  -0.0227   0.2875   1.0000
   3.750   0.6028   0.01967   0.00982  -0.0211   0.2822   1.0000
   4.000   0.6189   0.02022   0.01026  -0.0197   0.2781   1.0000
   4.250   0.6343   0.02077   0.01083  -0.0181   0.2746   1.0000
   4.500   0.6496   0.02126   0.01139  -0.0163   0.2709   1.0000
   4.750   0.6672   0.02184   0.01201  -0.0149   0.2670   1.0000
   5.000   0.6891   0.02254   0.01267  -0.0143   0.2628   1.0000
   5.250   0.7138   0.02352   0.01359  -0.0142   0.2589   1.0000
   5.500   0.7382   0.02424   0.01450  -0.0139   0.2554   1.0000
   5.750   0.7637   0.02512   0.01551  -0.0138   0.2520   1.0000
   6.000   0.7897   0.02604   0.01650  -0.0139   0.2485   1.0000
   6.250   0.8158   0.02708   0.01752  -0.0140   0.2449   1.0000
   6.500   0.8406   0.02836   0.01893  -0.0139   0.2415   1.0000
   6.750   0.8639   0.02950   0.02035  -0.0136   0.2384   1.0000
   7.000   0.8872   0.03072   0.02179  -0.0133   0.2350   1.0000
   7.250   0.9115   0.03186   0.02303  -0.0132   0.2311   1.0000
   7.500   0.9372   0.03322   0.02435  -0.0133   0.2274   1.0000
   7.750   0.9565   0.03496   0.02639  -0.0128   0.2240   1.0000
   8.000   0.9739   0.03655   0.02834  -0.0120   0.2195   1.0000
   8.250   0.9950   0.03790   0.02985  -0.0116   0.2149   1.0000
   8.500   1.0222   0.03915   0.03095  -0.0118   0.2105   1.0000
   8.750   1.0316   0.04146   0.03375  -0.0105   0.2060   1.0000
   9.000   1.0438   0.04344   0.03605  -0.0094   0.2007   1.0000
   9.250   1.0742   0.04388   0.03632  -0.0097   0.1952   1.0000
   9.500   1.0789   0.04671   0.03954  -0.0083   0.1902   1.0000
   9.750   1.0816   0.04924   0.04244  -0.0067   0.1844   1.0000
  10.000   1.1243   0.04848   0.04131  -0.0076   0.1781   1.0000
  10.250   1.1060   0.05277   0.04623  -0.0049   0.1733   1.0000
  10.500   1.1005   0.05573   0.04949  -0.0031   0.1680   1.0000
  10.750   1.1496   0.05407   0.04750  -0.0039   0.1609   1.0000
  11.000   1.1071   0.06000   0.05401  -0.0006   0.1580   1.0000
  11.250   1.0562   0.06625   0.06053   0.0020   0.1573   1.0000
  11.500   0.9818   0.07673   0.07116  -0.0001   0.1594   1.0000
  11.750   0.9043   0.09319   0.08766  -0.0092   0.1612   1.0000
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