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NACA 0012-64 (naca001264-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 0012-64 (naca001264-il)
Reynolds number: 50,000
Max Cl/Cd: 25.81 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca001264-il-50000-n5.txt
Download as CSV file: xf-naca001264-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0012-64                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.6817   0.09713   0.08914  -0.0318   1.0000   0.0743
 -11.500  -0.7196   0.08625   0.07823  -0.0389   1.0000   0.0730
 -11.250  -0.7633   0.07771   0.06957  -0.0428   1.0000   0.0716
 -11.000  -0.7983   0.07207   0.06375  -0.0427   1.0000   0.0711
 -10.750  -0.8228   0.06820   0.05971  -0.0405   1.0000   0.0712
 -10.500  -0.8407   0.06508   0.05642  -0.0374   1.0000   0.0718
 -10.250  -0.8525   0.06203   0.05317  -0.0345   1.0000   0.0727
 -10.000  -0.8614   0.05904   0.04992  -0.0314   1.0000   0.0737
  -9.750  -0.8676   0.05605   0.04664  -0.0283   1.0000   0.0747
  -9.500  -0.8706   0.05310   0.04335  -0.0251   1.0000   0.0757
  -9.250  -0.8700   0.05024   0.04012  -0.0221   1.0000   0.0765
  -9.000  -0.8660   0.04755   0.03704  -0.0192   1.0000   0.0776
  -8.750  -0.8596   0.04511   0.03414  -0.0163   1.0000   0.0792
  -8.500  -0.8479   0.04300   0.03182  -0.0143   1.0000   0.0814
  -8.250  -0.8328   0.04135   0.03011  -0.0127   1.0000   0.0839
  -8.000  -0.8170   0.03963   0.02817  -0.0110   1.0000   0.0865
  -7.750  -0.7989   0.03782   0.02610  -0.0095   1.0000   0.0889
  -7.500  -0.7786   0.03611   0.02409  -0.0082   1.0000   0.0916
  -7.250  -0.7568   0.03458   0.02242  -0.0072   1.0000   0.0951
  -7.000  -0.7369   0.03340   0.02124  -0.0060   1.0000   0.0999
  -6.750  -0.7146   0.03223   0.01989  -0.0050   1.0000   0.1057
  -6.500  -0.6916   0.03103   0.01870  -0.0041   1.0000   0.1112
  -6.250  -0.6698   0.02999   0.01761  -0.0030   1.0000   0.1183
  -6.000  -0.6504   0.02903   0.01665  -0.0016   1.0000   0.1277
  -5.750  -0.6320   0.02812   0.01574   0.0000   1.0000   0.1402
  -5.500  -0.6156   0.02721   0.01489   0.0019   1.0000   0.1556
  -5.250  -0.6007   0.02629   0.01408   0.0039   1.0000   0.1765
  -5.000  -0.5872   0.02531   0.01328   0.0061   1.0000   0.2063
  -4.750  -0.5754   0.02422   0.01252   0.0086   1.0000   0.2507
  -4.500  -0.5665   0.02296   0.01182   0.0115   1.0000   0.3240
  -4.250  -0.5599   0.02169   0.01144   0.0153   1.0000   0.4520
  -4.000  -0.5428   0.02125   0.01178   0.0188   1.0000   0.6028
  -3.750  -0.5176   0.02153   0.01225   0.0211   1.0000   0.6967
  -3.500  -0.4947   0.02192   0.01260   0.0234   1.0000   0.7554
  -3.250  -0.4680   0.02250   0.01309   0.0253   1.0000   0.8028
  -3.000  -0.4307   0.02333   0.01376   0.0253   1.0000   0.8409
  -2.750  -0.3927   0.02395   0.01419   0.0246   1.0000   0.8696
  -2.500  -0.3469   0.02458   0.01460   0.0222   1.0000   0.8969
  -2.250  -0.2744   0.02520   0.01498   0.0145   1.0000   0.9198
  -2.000  -0.2279   0.02525   0.01487   0.0106   1.0000   0.9361
  -1.750  -0.1909   0.02515   0.01465   0.0081   1.0000   0.9488
  -1.500  -0.1549   0.02502   0.01442   0.0056   1.0000   0.9608
  -1.250  -0.1182   0.02489   0.01420   0.0029   1.0000   0.9721
  -1.000  -0.0792   0.02472   0.01397  -0.0004   1.0000   0.9818
  -0.750  -0.0407   0.02456   0.01377  -0.0037   1.0000   0.9913
  -0.500  -0.0041   0.02442   0.01361  -0.0068   1.0000   1.0000
  -0.250  -0.0020   0.02438   0.01356  -0.0034   1.0000   1.0000
   0.000   0.0000   0.02436   0.01355   0.0000   1.0000   1.0000
   0.250   0.0020   0.02438   0.01356   0.0034   1.0000   1.0000
   0.500   0.0041   0.02442   0.01361   0.0068   1.0000   1.0000
   0.750   0.0407   0.02456   0.01377   0.0037   0.9914   1.0000
   1.000   0.0791   0.02472   0.01397   0.0004   0.9818   1.0000
   1.250   0.1182   0.02489   0.01420  -0.0029   0.9721   1.0000
   1.500   0.1548   0.02502   0.01441  -0.0056   0.9608   1.0000
   1.750   0.1908   0.02514   0.01464  -0.0081   0.9488   1.0000
   2.000   0.2279   0.02525   0.01486  -0.0106   0.9361   1.0000
   2.250   0.2743   0.02519   0.01497  -0.0145   0.9198   1.0000
   2.500   0.3470   0.02457   0.01460  -0.0222   0.8970   1.0000
   2.750   0.3926   0.02394   0.01418  -0.0246   0.8696   1.0000
   3.000   0.4306   0.02332   0.01375  -0.0253   0.8410   1.0000
   3.250   0.4680   0.02249   0.01308  -0.0253   0.8029   1.0000
   3.500   0.4946   0.02191   0.01260  -0.0234   0.7555   1.0000
   3.750   0.5175   0.02153   0.01225  -0.0210   0.6968   1.0000
   4.000   0.5427   0.02125   0.01178  -0.0187   0.6030   1.0000
   4.250   0.5598   0.02169   0.01143  -0.0153   0.4522   1.0000
   4.500   0.5664   0.02296   0.01181  -0.0114   0.3242   1.0000
   4.750   0.5753   0.02422   0.01251  -0.0085   0.2507   1.0000
   5.000   0.5871   0.02531   0.01328  -0.0061   0.2064   1.0000
   5.250   0.6007   0.02629   0.01408  -0.0039   0.1766   1.0000
   5.500   0.6156   0.02721   0.01488  -0.0019   0.1557   1.0000
   5.750   0.6320   0.02812   0.01573   0.0000   0.1403   1.0000
   6.000   0.6503   0.02903   0.01664   0.0016   0.1278   1.0000
   6.250   0.6698   0.02999   0.01761   0.0030   0.1183   1.0000
   6.500   0.6915   0.03102   0.01869   0.0041   0.1112   1.0000
   6.750   0.7146   0.03222   0.01988   0.0050   0.1058   1.0000
   7.000   0.7368   0.03340   0.02124   0.0060   0.0999   1.0000
   7.250   0.7568   0.03458   0.02242   0.0072   0.0951   1.0000
   7.500   0.7785   0.03611   0.02408   0.0082   0.0916   1.0000
   7.750   0.7989   0.03782   0.02609   0.0095   0.0889   1.0000
   8.000   0.8170   0.03962   0.02816   0.0110   0.0865   1.0000
   8.250   0.8328   0.04135   0.03011   0.0127   0.0839   1.0000
   8.500   0.8479   0.04300   0.03182   0.0143   0.0814   1.0000
   8.750   0.8596   0.04510   0.03413   0.0163   0.0792   1.0000
   9.000   0.8660   0.04755   0.03703   0.0192   0.0776   1.0000
   9.250   0.8701   0.05024   0.04012   0.0221   0.0765   1.0000
   9.500   0.8707   0.05310   0.04335   0.0251   0.0757   1.0000
   9.750   0.8677   0.05605   0.04664   0.0283   0.0747   1.0000
  10.000   0.8616   0.05904   0.04993   0.0314   0.0737   1.0000
  10.250   0.8528   0.06204   0.05318   0.0344   0.0727   1.0000
  10.500   0.8411   0.06509   0.05643   0.0373   0.0718   1.0000
  10.750   0.8235   0.06820   0.05971   0.0404   0.0712   1.0000
  11.000   0.7992   0.07206   0.06374   0.0426   0.0711   1.0000
  11.250   0.7641   0.07771   0.06957   0.0427   0.0716   1.0000
  11.500   0.7204   0.08628   0.07827   0.0388   0.0729   1.0000
  11.750   0.6825   0.09720   0.08921   0.0316   0.0742   1.0000
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