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NACA 64(1)-212 (n64212-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 64(1)-212 (n64212-il)
Reynolds number: 500,000
Max Cl/Cd: 67.76 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n64212-il-500000-n5.txt
Download as CSV file: xf-n64212-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.8726   0.06656   0.06376  -0.0405   1.0000   0.0102
 -13.750  -0.9037   0.05782   0.05479  -0.0462   1.0000   0.0102
 -13.500  -0.9294   0.05106   0.04780  -0.0499   1.0000   0.0102
 -13.250  -0.9466   0.04611   0.04263  -0.0519   1.0000   0.0103
 -13.000  -0.9591   0.04210   0.03842  -0.0528   1.0000   0.0103
 -12.750  -0.9662   0.03898   0.03509  -0.0530   1.0000   0.0106
 -12.500  -0.9730   0.03607   0.03198  -0.0525   1.0000   0.0107
 -12.250  -0.9775   0.03354   0.02922  -0.0514   1.0000   0.0108
 -12.000  -0.9771   0.03163   0.02713  -0.0500   1.0000   0.0110
 -11.750  -0.9754   0.02998   0.02529  -0.0481   1.0000   0.0112
 -11.500  -0.9705   0.02862   0.02375  -0.0460   1.0000   0.0113
 -11.250  -0.9630   0.02694   0.02189  -0.0444   1.0000   0.0115
 -11.000  -0.9513   0.02563   0.02046  -0.0432   1.0000   0.0118
 -10.750  -0.9358   0.02469   0.01945  -0.0422   1.0000   0.0120
 -10.500  -0.9174   0.02415   0.01887  -0.0414   1.0000   0.0124
 -10.250  -0.9003   0.02322   0.01784  -0.0404   1.0000   0.0127
 -10.000  -0.8818   0.02249   0.01704  -0.0396   1.0000   0.0131
  -9.750  -0.8637   0.02162   0.01606  -0.0386   1.0000   0.0134
  -9.500  -0.8458   0.02072   0.01505  -0.0375   1.0000   0.0138
  -9.250  -0.8167   0.01973   0.01391  -0.0387   0.9874   0.0142
  -9.000  -0.7851   0.01883   0.01288  -0.0403   0.9749   0.0146
  -8.750  -0.7539   0.01792   0.01186  -0.0418   0.9630   0.0150
  -8.500  -0.7246   0.01707   0.01096  -0.0429   0.9497   0.0157
  -8.250  -0.6976   0.01651   0.01032  -0.0433   0.9358   0.0162
  -8.000  -0.6732   0.01597   0.00970  -0.0430   0.9215   0.0167
  -7.750  -0.6500   0.01544   0.00909  -0.0425   0.9084   0.0171
  -7.500  -0.6269   0.01494   0.00850  -0.0419   0.8959   0.0177
  -7.250  -0.6037   0.01446   0.00791  -0.0412   0.8847   0.0183
  -7.000  -0.5799   0.01404   0.00738  -0.0407   0.8736   0.0189
  -6.750  -0.5562   0.01355   0.00682  -0.0402   0.8630   0.0197
  -6.500  -0.5320   0.01310   0.00632  -0.0398   0.8533   0.0207
  -6.250  -0.5070   0.01275   0.00591  -0.0395   0.8436   0.0218
  -6.000  -0.4816   0.01241   0.00550  -0.0392   0.8343   0.0229
  -5.750  -0.4559   0.01211   0.00512  -0.0389   0.8255   0.0241
  -5.500  -0.4301   0.01177   0.00471  -0.0387   0.8163   0.0256
  -5.250  -0.4042   0.01144   0.00434  -0.0385   0.8079   0.0278
  -5.000  -0.3777   0.01119   0.00404  -0.0384   0.7992   0.0301
  -4.750  -0.3508   0.01097   0.00376  -0.0384   0.7913   0.0325
  -4.500  -0.3242   0.01070   0.00346  -0.0383   0.7831   0.0371
  -4.250  -0.2971   0.01049   0.00322  -0.0383   0.7751   0.0416
  -4.000  -0.2702   0.01025   0.00298  -0.0382   0.7668   0.0511
  -3.750  -0.2434   0.00995   0.00275  -0.0382   0.7589   0.0712
  -3.500  -0.2169   0.00957   0.00249  -0.0383   0.7511   0.1120
  -3.250  -0.1908   0.00905   0.00223  -0.0384   0.7437   0.1844
  -3.000  -0.1652   0.00838   0.00193  -0.0385   0.7362   0.2909
  -2.750  -0.1399   0.00764   0.00170  -0.0387   0.7291   0.4319
  -2.500  -0.1124   0.00745   0.00162  -0.0387   0.7215   0.4817
  -2.250  -0.0844   0.00735   0.00156  -0.0388   0.7142   0.5120
  -2.000  -0.0568   0.00723   0.00154  -0.0388   0.7066   0.5555
  -1.750  -0.0292   0.00714   0.00156  -0.0388   0.6997   0.5951
  -1.500  -0.0009   0.00712   0.00154  -0.0389   0.6927   0.6101
  -1.250   0.0276   0.00712   0.00150  -0.0390   0.6864   0.6184
  -1.000   0.0562   0.00710   0.00148  -0.0391   0.6796   0.6261
  -0.500   0.1133   0.00711   0.00145  -0.0394   0.6666   0.6387
  -0.250   0.1419   0.00713   0.00144  -0.0395   0.6600   0.6451
   0.000   0.1704   0.00713   0.00144  -0.0397   0.6537   0.6508
   0.250   0.1990   0.00715   0.00146  -0.0398   0.6475   0.6573
   0.500   0.2275   0.00718   0.00147  -0.0400   0.6420   0.6638
   0.750   0.2561   0.00718   0.00151  -0.0401   0.6362   0.6708
   1.000   0.2846   0.00722   0.00155  -0.0403   0.6303   0.6779
   1.250   0.3130   0.00724   0.00160  -0.0404   0.6245   0.6847
   1.500   0.3415   0.00728   0.00165  -0.0405   0.6174   0.6919
   1.750   0.3697   0.00732   0.00171  -0.0406   0.6100   0.6987
   2.000   0.3980   0.00736   0.00178  -0.0407   0.6020   0.7062
   2.250   0.4261   0.00741   0.00185  -0.0408   0.5925   0.7134
   2.500   0.4535   0.00749   0.00191  -0.0407   0.5718   0.7216
   2.750   0.4800   0.00763   0.00197  -0.0404   0.5398   0.7293
   3.000   0.5066   0.00780   0.00205  -0.0402   0.5080   0.7376
   3.250   0.5329   0.00800   0.00218  -0.0400   0.4715   0.7451
   3.500   0.5590   0.00825   0.00232  -0.0398   0.4316   0.7534
   3.750   0.5814   0.00892   0.00262  -0.0391   0.3375   0.7612
   4.000   0.6025   0.00980   0.00307  -0.0385   0.2353   0.7700
   4.250   0.6248   0.01050   0.00349  -0.0379   0.1614   0.7787
   4.500   0.6478   0.01112   0.00388  -0.0373   0.1059   0.7877
   5.000   0.6955   0.01207   0.00459  -0.0364   0.0477   0.8057
   5.250   0.7204   0.01240   0.00493  -0.0360   0.0389   0.8154
   5.500   0.7450   0.01270   0.00526  -0.0356   0.0339   0.8250
   5.750   0.7697   0.01301   0.00561  -0.0352   0.0304   0.8349
   6.000   0.7935   0.01338   0.00602  -0.0346   0.0271   0.8457
   6.250   0.8174   0.01366   0.00639  -0.0340   0.0252   0.8566
   6.500   0.8406   0.01401   0.00678  -0.0333   0.0232   0.8680
   6.750   0.8621   0.01446   0.00728  -0.0323   0.0211   0.8810
   7.000   0.8839   0.01481   0.00773  -0.0313   0.0201   0.8950
   7.250   0.9045   0.01518   0.00819  -0.0301   0.0190   0.9116
   7.500   0.9242   0.01556   0.00863  -0.0287   0.0180   0.9317
   7.750   0.9465   0.01598   0.00911  -0.0280   0.0170   0.9599
   8.000   0.9710   0.01667   0.00983  -0.0280   0.0161   1.0000
   8.250   0.9931   0.01721   0.01043  -0.0274   0.0156   1.0000
   8.500   1.0141   0.01783   0.01111  -0.0267   0.0152   1.0000
   8.750   1.0342   0.01849   0.01182  -0.0258   0.0147   1.0000
   9.000   1.0537   0.01916   0.01255  -0.0249   0.0143   1.0000
   9.250   1.0723   0.01987   0.01332  -0.0238   0.0140   1.0000
   9.500   1.0902   0.02059   0.01409  -0.0227   0.0136   1.0000
   9.750   1.1065   0.02132   0.01488  -0.0214   0.0134   1.0000
  10.000   1.1207   0.02210   0.01571  -0.0197   0.0131   1.0000
  10.250   1.1334   0.02298   0.01665  -0.0179   0.0129   1.0000
  10.500   1.1447   0.02402   0.01775  -0.0161   0.0126   1.0000
  10.750   1.1539   0.02532   0.01914  -0.0142   0.0123   1.0000
  11.000   1.1666   0.02632   0.02023  -0.0128   0.0122   1.0000
  11.250   1.1792   0.02734   0.02136  -0.0115   0.0119   1.0000
  11.500   1.1902   0.02855   0.02269  -0.0102   0.0117   1.0000
  11.750   1.2003   0.02989   0.02415  -0.0089   0.0116   1.0000
  12.000   1.2098   0.03129   0.02567  -0.0076   0.0114   1.0000
  12.250   1.2180   0.03285   0.02736  -0.0065   0.0112   1.0000
  12.500   1.2256   0.03447   0.02910  -0.0054   0.0110   1.0000
  12.750   1.2322   0.03621   0.03098  -0.0045   0.0108   1.0000
  13.000   1.2374   0.03814   0.03304  -0.0036   0.0107   1.0000
  13.250   1.2416   0.04018   0.03521  -0.0029   0.0105   1.0000
  13.500   1.2449   0.04235   0.03751  -0.0024   0.0104   1.0000
  13.750   1.2474   0.04465   0.03993  -0.0020   0.0103   1.0000
  14.000   1.2503   0.04691   0.04229  -0.0020   0.0101   1.0000
  14.250   1.2510   0.04955   0.04505  -0.0021   0.0100   1.0000
  14.500   1.2512   0.05232   0.04792  -0.0024   0.0098   1.0000
  14.750   1.2483   0.05561   0.05133  -0.0030   0.0097   1.0000
  15.000   1.2424   0.05945   0.05532  -0.0039   0.0096   1.0000
  15.250   1.2353   0.06362   0.05963  -0.0052   0.0095   1.0000
  15.500   1.2241   0.06868   0.06485  -0.0071   0.0095   1.0000
  15.750   1.2102   0.07446   0.07081  -0.0096   0.0094   1.0000
  16.000   1.1925   0.08128   0.07782  -0.0129   0.0093   1.0000
  16.500   1.1563   0.09666   0.09357  -0.0217   0.0093   1.0000
  16.750   1.1321   0.10658   0.10369  -0.0277   0.0093   1.0000
  17.250   1.0776   0.13053   0.12805  -0.0429   0.0094   1.0000
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