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NACA 64(1)-212 (n64212-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 64(1)-212 (n64212-il)
Reynolds number: 50,000
Max Cl/Cd: 31.75 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n64212-il-50000-n5.txt
Download as CSV file: xf-n64212-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(1)-212                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5635   0.09582   0.08852  -0.0309   1.0000   0.0572
 -10.500  -0.5796   0.08754   0.08027  -0.0367   1.0000   0.0560
 -10.250  -0.6070   0.07940   0.07212  -0.0430   1.0000   0.0546
 -10.000  -0.6397   0.07290   0.06552  -0.0470   1.0000   0.0536
  -9.750  -0.6742   0.06829   0.06069  -0.0476   1.0000   0.0526
  -9.500  -0.6898   0.06444   0.05659  -0.0472   1.0000   0.0523
  -9.250  -0.6958   0.06080   0.05270  -0.0464   1.0000   0.0523
  -9.000  -0.6973   0.05729   0.04892  -0.0455   1.0000   0.0523
  -8.750  -0.6951   0.05390   0.04526  -0.0444   1.0000   0.0525
  -8.500  -0.6896   0.05073   0.04183  -0.0432   1.0000   0.0529
  -8.250  -0.6816   0.04783   0.03867  -0.0420   1.0000   0.0535
  -8.000  -0.6706   0.04539   0.03605  -0.0408   1.0000   0.0548
  -7.750  -0.6592   0.04321   0.03366  -0.0394   1.0000   0.0568
  -7.500  -0.6473   0.04102   0.03115  -0.0378   1.0000   0.0588
  -7.250  -0.6339   0.03882   0.02861  -0.0360   1.0000   0.0605
  -7.000  -0.6183   0.03674   0.02618  -0.0343   1.0000   0.0619
  -6.750  -0.6013   0.03494   0.02403  -0.0326   1.0000   0.0634
  -6.500  -0.5845   0.03328   0.02241  -0.0311   1.0000   0.0663
  -6.250  -0.5682   0.03205   0.02111  -0.0294   1.0000   0.0701
  -6.000  -0.5506   0.03086   0.01975  -0.0276   1.0000   0.0739
  -5.750  -0.5330   0.02978   0.01853  -0.0255   1.0000   0.0770
  -5.500  -0.5195   0.02876   0.01760  -0.0234   1.0000   0.0820
  -5.250  -0.5059   0.02796   0.01667  -0.0213   1.0000   0.0886
  -5.000  -0.4940   0.02704   0.01574  -0.0191   1.0000   0.0943
  -4.750  -0.4817   0.02622   0.01485  -0.0171   1.0000   0.1027
  -4.500  -0.4533   0.02500   0.01371  -0.0185   0.9927   0.1216
  -4.250  -0.4226   0.02328   0.01236  -0.0208   0.9839   0.1696
  -4.000  -0.4033   0.02093   0.01198  -0.0209   0.9748   0.4708
  -3.750  -0.3762   0.02128   0.01250  -0.0198   0.9648   0.5954
  -3.500  -0.3521   0.02211   0.01339  -0.0171   0.9551   0.6678
  -3.250  -0.3299   0.02337   0.01468  -0.0126   0.9465   0.7268
  -3.000  -0.3042   0.02401   0.01517  -0.0102   0.9376   0.7581
  -2.750  -0.2716   0.02403   0.01496  -0.0110   0.9295   0.7727
  -2.500  -0.2377   0.02395   0.01465  -0.0124   0.9215   0.7845
  -2.250  -0.2040   0.02391   0.01440  -0.0135   0.9137   0.7941
  -2.000  -0.1706   0.02380   0.01411  -0.0150   0.9058   0.8043
  -1.750  -0.1411   0.02370   0.01385  -0.0157   0.8972   0.8141
  -1.500  -0.1068   0.02361   0.01362  -0.0172   0.8900   0.8224
  -1.250  -0.0803   0.02352   0.01341  -0.0175   0.8808   0.8325
  -1.000  -0.0455   0.02346   0.01325  -0.0189   0.8742   0.8406
  -0.750  -0.0198   0.02342   0.01312  -0.0190   0.8652   0.8503
  -0.500   0.0133   0.02335   0.01298  -0.0203   0.8586   0.8600
  -0.250   0.0400   0.02337   0.01296  -0.0205   0.8499   0.8695
   0.000   0.0729   0.02334   0.01288  -0.0217   0.8435   0.8795
   0.250   0.0991   0.02339   0.01291  -0.0219   0.8349   0.8908
   0.500   0.1356   0.02340   0.01291  -0.0238   0.8289   0.9001
   0.750   0.1659   0.02348   0.01300  -0.0249   0.8211   0.9113
   1.000   0.1999   0.02353   0.01307  -0.0265   0.8144   0.9229
   1.250   0.2383   0.02361   0.01319  -0.0290   0.8083   0.9332
   1.500   0.2752   0.02374   0.01339  -0.0314   0.8008   0.9442
   1.750   0.3191   0.02376   0.01347  -0.0348   0.7960   0.9540
   2.000   0.3561   0.02402   0.01384  -0.0377   0.7876   0.9661
   2.250   0.4012   0.02408   0.01401  -0.0415   0.7820   0.9761
   2.500   0.4412   0.02431   0.01439  -0.0449   0.7738   0.9888
   2.750   0.4782   0.02442   0.01464  -0.0472   0.7669   1.0000
   3.000   0.4830   0.02484   0.01512  -0.0442   0.7564   1.0000
   3.250   0.5043   0.02492   0.01529  -0.0432   0.7495   1.0000
   3.750   0.5263   0.02583   0.01636  -0.0388   0.7287   1.0000
   4.000   0.5517   0.02600   0.01666  -0.0384   0.7204   1.0000
   4.250   0.5698   0.02642   0.01721  -0.0371   0.7087   1.0000
   4.500   0.5936   0.02656   0.01754  -0.0362   0.6963   1.0000
   4.750   0.6204   0.02634   0.01749  -0.0351   0.6806   1.0000
   5.000   0.6535   0.02517   0.01647  -0.0332   0.6565   1.0000
   5.250   0.6761   0.02405   0.01543  -0.0298   0.6184   1.0000
   5.500   0.6962   0.02311   0.01452  -0.0263   0.5700   1.0000
   5.750   0.7123   0.02277   0.01417  -0.0231   0.5082   1.0000
   6.000   0.7256   0.02285   0.01380  -0.0196   0.3764   1.0000
   6.250   0.7241   0.02484   0.01447  -0.0156   0.2211   1.0000
   6.500   0.7253   0.02711   0.01609  -0.0131   0.1524   1.0000
   6.750   0.7320   0.02897   0.01767  -0.0111   0.1230   1.0000
   7.000   0.7416   0.03062   0.01918  -0.0094   0.1076   1.0000
   7.250   0.7542   0.03210   0.02064  -0.0078   0.0952   1.0000
   7.500   0.7704   0.03349   0.02211  -0.0065   0.0862   1.0000
   7.750   0.7905   0.03501   0.02356  -0.0056   0.0796   1.0000
   8.000   0.8176   0.03637   0.02514  -0.0052   0.0719   1.0000
   8.250   0.8514   0.03816   0.02686  -0.0056   0.0670   1.0000
   8.500   0.8829   0.04000   0.02904  -0.0057   0.0622   1.0000
   8.750   0.9081   0.04192   0.03108  -0.0056   0.0581   1.0000
   9.000   0.9366   0.04458   0.03377  -0.0060   0.0557   1.0000
   9.250   0.9568   0.04730   0.03697  -0.0053   0.0544   1.0000
   9.500   0.9711   0.05019   0.04032  -0.0042   0.0529   1.0000
   9.750   0.9805   0.05312   0.04366  -0.0030   0.0512   1.0000
  10.000   0.9862   0.05603   0.04690  -0.0016   0.0497   1.0000
  10.250   0.9891   0.05902   0.05019  -0.0003   0.0486   1.0000
  10.500   0.9875   0.06219   0.05365   0.0012   0.0479   1.0000
  10.750   0.9794   0.06552   0.05725   0.0030   0.0476   1.0000
  11.000   0.9663   0.06915   0.06115   0.0043   0.0477   1.0000
  11.250   0.9492   0.07325   0.06550   0.0048   0.0477   1.0000
  11.500   0.9277   0.07807   0.07056   0.0042   0.0479   1.0000
  11.750   0.9020   0.08386   0.07657   0.0021   0.0483   1.0000
  12.000   0.8727   0.09102   0.08391  -0.0016   0.0488   1.0000
  12.250   0.8418   0.09983   0.09285  -0.0073   0.0496   1.0000
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