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NACA 64-012A AIRFOIL (n64012a-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 64-012A AIRFOIL (n64012a-il)
Reynolds number: 500,000
Max Cl/Cd: 56.37 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n64012a-il-500000.txt
Download as CSV file: xf-n64012a-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-012A AIRFOIL                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.9467   0.05400   0.05061  -0.0321   1.0000   0.0169
 -11.750  -0.9627   0.05048   0.04686  -0.0311   1.0000   0.0168
 -11.500  -0.9763   0.04741   0.04358  -0.0291   1.0000   0.0168
 -11.250  -0.9899   0.04424   0.04017  -0.0261   1.0000   0.0168
 -11.000  -1.0004   0.04048   0.03613  -0.0232   1.0000   0.0169
 -10.750  -1.0002   0.03740   0.03283  -0.0211   1.0000   0.0172
 -10.500  -0.9896   0.03584   0.03120  -0.0198   1.0000   0.0176
 -10.250  -0.9748   0.03479   0.03011  -0.0188   1.0000   0.0181
 -10.000  -0.9660   0.03221   0.02726  -0.0169   1.0000   0.0182
  -9.750  -0.9541   0.02982   0.02459  -0.0152   1.0000   0.0184
  -9.500  -0.9390   0.02783   0.02237  -0.0138   1.0000   0.0187
  -9.250  -0.9219   0.02608   0.02042  -0.0126   1.0000   0.0190
  -9.000  -0.9033   0.02451   0.01867  -0.0114   1.0000   0.0194
  -8.750  -0.8837   0.02317   0.01717  -0.0103   1.0000   0.0199
  -8.500  -0.8633   0.02217   0.01603  -0.0093   1.0000   0.0206
  -8.250  -0.8425   0.02138   0.01511  -0.0082   1.0000   0.0211
  -8.000  -0.8219   0.02052   0.01415  -0.0071   1.0000   0.0214
  -7.750  -0.8050   0.01844   0.01198  -0.0056   1.0000   0.0221
  -7.500  -0.7881   0.01743   0.01095  -0.0039   1.0000   0.0228
  -7.250  -0.7709   0.01673   0.01023  -0.0021   1.0000   0.0235
  -7.000  -0.7541   0.01612   0.00960  -0.0003   1.0000   0.0243
  -6.750  -0.7385   0.01557   0.00901   0.0018   1.0000   0.0252
  -6.500  -0.7238   0.01513   0.00854   0.0041   1.0000   0.0263
  -6.250  -0.6912   0.01466   0.00802   0.0027   0.9972   0.0274
  -6.000  -0.6588   0.01344   0.00676   0.0009   0.9929   0.0299
  -5.750  -0.6238   0.01288   0.00618  -0.0010   0.9879   0.0326
  -5.500  -0.5871   0.01230   0.00555  -0.0033   0.9841   0.0362
  -5.250  -0.5539   0.01174   0.00500  -0.0048   0.9773   0.0432
  -5.000  -0.5195   0.01119   0.00448  -0.0065   0.9710   0.0553
  -4.750  -0.4903   0.01054   0.00400  -0.0071   0.9604   0.0857
  -4.500  -0.4643   0.00966   0.00351  -0.0074   0.9488   0.1697
  -4.250  -0.4443   0.00847   0.00298  -0.0066   0.9350   0.3208
  -4.000  -0.4256   0.00755   0.00266  -0.0052   0.9208   0.4704
  -3.750  -0.4016   0.00728   0.00253  -0.0044   0.9080   0.5282
  -3.500  -0.3765   0.00714   0.00242  -0.0037   0.8955   0.5636
  -3.250  -0.3509   0.00704   0.00234  -0.0032   0.8829   0.5871
  -3.000  -0.3246   0.00699   0.00226  -0.0027   0.8712   0.6065
  -2.750  -0.2983   0.00694   0.00219  -0.0023   0.8601   0.6244
  -2.250  -0.2458   0.00688   0.00212  -0.0014   0.8384   0.6616
  -2.000  -0.2194   0.00689   0.00212  -0.0010   0.8284   0.6810
  -1.500  -0.1655   0.00687   0.00207  -0.0005   0.8089   0.7047
  -1.250  -0.1381   0.00687   0.00203  -0.0003   0.7996   0.7147
  -1.000  -0.1106   0.00686   0.00199  -0.0002   0.7905   0.7228
  -0.750  -0.0829   0.00684   0.00197  -0.0002   0.7814   0.7308
  -0.500  -0.0554   0.00686   0.00194  -0.0001   0.7733   0.7392
  -0.250  -0.0277   0.00683   0.00193  -0.0001   0.7639   0.7471
   0.000   0.0000   0.00685   0.00192   0.0000   0.7557   0.7557
   0.250   0.0276   0.00683   0.00193   0.0001   0.7471   0.7639
   0.500   0.0553   0.00686   0.00194   0.0001   0.7391   0.7733
   0.750   0.0829   0.00684   0.00197   0.0002   0.7308   0.7814
   1.000   0.1106   0.00686   0.00199   0.0002   0.7228   0.7905
   1.250   0.1380   0.00687   0.00203   0.0004   0.7147   0.7996
   1.500   0.1654   0.00687   0.00207   0.0005   0.7047   0.8089
   2.000   0.2194   0.00689   0.00212   0.0010   0.6809   0.8284
   2.250   0.2457   0.00688   0.00212   0.0015   0.6615   0.8384
   2.750   0.2983   0.00694   0.00219   0.0023   0.6244   0.8602
   3.000   0.3246   0.00699   0.00226   0.0027   0.6066   0.8712
   3.250   0.3509   0.00704   0.00234   0.0032   0.5872   0.8829
   3.500   0.3765   0.00714   0.00242   0.0037   0.5636   0.8955
   3.750   0.4016   0.00728   0.00253   0.0044   0.5280   0.9081
   4.000   0.4256   0.00755   0.00266   0.0052   0.4704   0.9208
   4.250   0.4444   0.00846   0.00298   0.0066   0.3212   0.9350
   4.500   0.4643   0.00966   0.00351   0.0074   0.1695   0.9489
   4.750   0.4903   0.01054   0.00400   0.0071   0.0858   0.9605
   5.000   0.5195   0.01119   0.00448   0.0065   0.0553   0.9710
   5.250   0.5539   0.01174   0.00500   0.0048   0.0432   0.9773
   5.500   0.5872   0.01231   0.00556   0.0032   0.0361   0.9841
   5.750   0.6239   0.01288   0.00618   0.0010   0.0326   0.9880
   6.000   0.6589   0.01344   0.00676  -0.0010   0.0299   0.9930
   6.250   0.6915   0.01466   0.00802  -0.0027   0.0274   0.9973
   6.500   0.7235   0.01512   0.00853  -0.0040   0.0263   1.0000
   6.750   0.7383   0.01556   0.00901  -0.0018   0.0252   1.0000
   7.000   0.7539   0.01611   0.00959   0.0003   0.0243   1.0000
   7.250   0.7707   0.01673   0.01022   0.0022   0.0235   1.0000
   7.500   0.7880   0.01743   0.01095   0.0039   0.0228   1.0000
   7.750   0.8050   0.01844   0.01198   0.0056   0.0221   1.0000
   8.000   0.8220   0.02052   0.01414   0.0071   0.0214   1.0000
   8.250   0.8426   0.02137   0.01511   0.0082   0.0211   1.0000
   8.500   0.8634   0.02218   0.01604   0.0093   0.0206   1.0000
   8.750   0.8839   0.02316   0.01717   0.0103   0.0199   1.0000
   9.000   0.9036   0.02451   0.01868   0.0114   0.0194   1.0000
   9.250   0.9222   0.02608   0.02042   0.0125   0.0190   1.0000
   9.500   0.9393   0.02784   0.02238   0.0138   0.0187   1.0000
   9.750   0.9544   0.02984   0.02461   0.0152   0.0184   1.0000
  10.000   0.9664   0.03222   0.02727   0.0168   0.0182   1.0000
  10.250   0.9753   0.03480   0.03012   0.0187   0.0180   1.0000
  10.500   0.9902   0.03584   0.03120   0.0197   0.0176   1.0000
  10.750   1.0008   0.03742   0.03285   0.0210   0.0172   1.0000
  11.000   1.0008   0.04056   0.03621   0.0231   0.0169   1.0000
  11.250   0.9900   0.04436   0.04030   0.0260   0.0168   1.0000
  11.500   0.9766   0.04751   0.04369   0.0290   0.0167   1.0000
  11.750   0.9631   0.05059   0.04699   0.0309   0.0168   1.0000
  12.000   0.9471   0.05411   0.05074   0.0318   0.0169   1.0000
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