Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 65(1)-212 (naca651212-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 65(1)-212 (naca651212-il)
Reynolds number: 200,000
Max Cl/Cd: 52.86 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca651212-il-200000-n5.txt
Download as CSV file: xf-naca651212-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(1)-212                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.5657   0.08916   0.08550  -0.0376   1.0000   0.0186
 -11.000  -0.5998   0.07419   0.07050  -0.0485   1.0000   0.0180
 -10.750  -0.6338   0.06512   0.06129  -0.0542   1.0000   0.0177
 -10.500  -0.6680   0.05826   0.05423  -0.0565   1.0000   0.0174
 -10.250  -0.6827   0.05506   0.05091  -0.0561   1.0000   0.0176
 -10.000  -0.7051   0.05142   0.04710  -0.0539   1.0000   0.0175
  -9.750  -0.7115   0.04935   0.04491  -0.0517   1.0000   0.0178
  -9.500  -0.7174   0.04680   0.04219  -0.0494   1.0000   0.0182
  -9.250  -0.7232   0.04413   0.03931  -0.0466   1.0000   0.0185
  -9.000  -0.7305   0.04150   0.03645  -0.0429   1.0000   0.0187
  -8.750  -0.7164   0.03748   0.03199  -0.0436   0.9892   0.0190
  -8.500  -0.6957   0.03388   0.02791  -0.0448   0.9806   0.0195
  -8.250  -0.6714   0.03088   0.02443  -0.0458   0.9732   0.0203
  -8.000  -0.6452   0.02880   0.02186  -0.0466   0.9655   0.0214
  -7.750  -0.6188   0.02659   0.01932  -0.0473   0.9582   0.0221
  -7.500  -0.5906   0.02470   0.01726  -0.0483   0.9517   0.0228
  -7.250  -0.5628   0.02336   0.01579  -0.0489   0.9444   0.0234
  -7.000  -0.5343   0.02215   0.01442  -0.0495   0.9374   0.0242
  -6.750  -0.5075   0.02112   0.01325  -0.0497   0.9296   0.0251
  -6.500  -0.4806   0.02028   0.01230  -0.0499   0.9221   0.0266
  -6.250  -0.4552   0.01946   0.01136  -0.0496   0.9140   0.0278
  -6.000  -0.4300   0.01862   0.01040  -0.0493   0.9064   0.0285
  -5.750  -0.4074   0.01771   0.00943  -0.0485   0.8981   0.0294
  -5.500  -0.3856   0.01680   0.00849  -0.0478   0.8907   0.0308
  -5.250  -0.3635   0.01617   0.00783  -0.0470   0.8825   0.0322
  -5.000  -0.3401   0.01566   0.00727  -0.0464   0.8755   0.0347
  -4.750  -0.3168   0.01521   0.00673  -0.0458   0.8676   0.0371
  -4.500  -0.2934   0.01469   0.00611  -0.0452   0.8611   0.0397
  -4.250  -0.2698   0.01421   0.00560  -0.0446   0.8539   0.0437
  -4.000  -0.2450   0.01387   0.00516  -0.0442   0.8474   0.0498
  -3.750  -0.2209   0.01340   0.00474  -0.0438   0.8409   0.0646
  -3.500  -0.1990   0.01262   0.00429  -0.0432   0.8340   0.1395
  -3.250  -0.1830   0.01105   0.00373  -0.0423   0.8282   0.3787
  -3.000  -0.1633   0.01034   0.00373  -0.0410   0.8214   0.5587
  -2.750  -0.1388   0.01026   0.00383  -0.0401   0.8160   0.6293
  -2.500  -0.1143   0.01037   0.00403  -0.0390   0.8100   0.6809
  -2.250  -0.0889   0.01048   0.00417  -0.0381   0.8042   0.7064
  -2.000  -0.0620   0.01052   0.00414  -0.0377   0.7997   0.7192
  -1.750  -0.0343   0.01050   0.00405  -0.0378   0.7938   0.7267
  -1.500  -0.0067   0.01048   0.00398  -0.0377   0.7883   0.7312
  -1.250   0.0212   0.01046   0.00388  -0.0377   0.7838   0.7363
  -1.000   0.0491   0.01045   0.00383  -0.0379   0.7780   0.7422
  -0.750   0.0767   0.01045   0.00380  -0.0378   0.7730   0.7466
  -0.500   0.1046   0.01045   0.00375  -0.0379   0.7687   0.7517
  -0.250   0.1325   0.01045   0.00374  -0.0380   0.7629   0.7577
   0.000   0.1599   0.01046   0.00375  -0.0380   0.7581   0.7620
   0.250   0.1879   0.01047   0.00374  -0.0380   0.7540   0.7673
   0.500   0.2157   0.01050   0.00378  -0.0382   0.7483   0.7733
   0.750   0.2430   0.01052   0.00383  -0.0380   0.7435   0.7779
   1.000   0.2709   0.01055   0.00386  -0.0381   0.7395   0.7836
   1.250   0.2984   0.01059   0.00395  -0.0382   0.7340   0.7893
   1.500   0.3256   0.01063   0.00404  -0.0380   0.7291   0.7944
   1.750   0.3535   0.01067   0.00410  -0.0381   0.7250   0.8006
   2.000   0.3806   0.01073   0.00424  -0.0380   0.7197   0.8062
   2.250   0.4077   0.01079   0.00437  -0.0379   0.7145   0.8119
   2.500   0.4357   0.01084   0.00445  -0.0380   0.7101   0.8186
   2.750   0.4617   0.01089   0.00463  -0.0376   0.7028   0.8241
   3.000   0.4882   0.01088   0.00466  -0.0372   0.6918   0.8310
   3.250   0.5128   0.01081   0.00462  -0.0362   0.6713   0.8372
   3.500   0.5363   0.01073   0.00449  -0.0349   0.6376   0.8440
   3.750   0.5582   0.01077   0.00440  -0.0335   0.5874   0.8512
   4.000   0.5793   0.01096   0.00443  -0.0320   0.5258   0.8588
   4.250   0.5920   0.01173   0.00461  -0.0292   0.3933   0.8673
   4.500   0.5984   0.01322   0.00530  -0.0261   0.2283   0.8775
   4.750   0.6078   0.01448   0.00597  -0.0235   0.1066   0.8872
   5.000   0.6236   0.01528   0.00654  -0.0216   0.0601   0.8978
   5.250   0.6422   0.01583   0.00705  -0.0202   0.0463   0.9092
   5.500   0.6615   0.01630   0.00757  -0.0188   0.0407   0.9215
   5.750   0.6815   0.01678   0.00815  -0.0176   0.0369   0.9350
   6.000   0.7012   0.01752   0.00892  -0.0166   0.0333   0.9512
   6.250   0.7289   0.01809   0.00960  -0.0171   0.0308   0.9683
   6.500   0.7554   0.01882   0.01040  -0.0177   0.0288   1.0000
   6.750   0.7747   0.01959   0.01120  -0.0169   0.0274   1.0000
   7.000   0.7932   0.02047   0.01210  -0.0159   0.0263   1.0000
   7.250   0.8103   0.02168   0.01331  -0.0148   0.0253   1.0000
   7.500   0.8305   0.02281   0.01448  -0.0140   0.0246   1.0000
   7.750   0.8526   0.02377   0.01553  -0.0134   0.0239   1.0000
   8.000   0.8750   0.02476   0.01663  -0.0130   0.0229   1.0000
   8.250   0.8974   0.02580   0.01776  -0.0125   0.0219   1.0000
   8.500   0.9199   0.02698   0.01904  -0.0121   0.0211   1.0000
   8.750   0.9425   0.02830   0.02048  -0.0118   0.0206   1.0000
   9.000   0.9640   0.02969   0.02200  -0.0114   0.0200   1.0000
   9.250   0.9848   0.03122   0.02366  -0.0109   0.0196   1.0000
   9.500   1.0046   0.03300   0.02559  -0.0104   0.0192   1.0000
   9.750   1.0229   0.03538   0.02815  -0.0098   0.0188   1.0000
  10.000   1.0356   0.03768   0.03075  -0.0084   0.0184   1.0000
  10.250   1.0443   0.03967   0.03308  -0.0065   0.0180   1.0000
  10.500   1.0478   0.04181   0.03557  -0.0040   0.0174   1.0000
  10.750   1.0473   0.04447   0.03855  -0.0013   0.0171   1.0000
  11.000   1.0429   0.04726   0.04166   0.0014   0.0169   1.0000
  11.250   1.0346   0.05030   0.04499   0.0038   0.0168   1.0000
  11.500   1.0230   0.05364   0.04860   0.0059   0.0167   1.0000
  11.750   1.0080   0.05741   0.05263   0.0074   0.0165   1.0000
  12.000   0.9907   0.06160   0.05706   0.0082   0.0165   1.0000
  12.250   0.9710   0.06635   0.06205   0.0081   0.0165   1.0000
  12.500   0.9496   0.07173   0.06764   0.0069   0.0166   1.0000
  12.750   0.9247   0.07820   0.07431   0.0044   0.0166   1.0000
  13.000   0.8983   0.08576   0.08203   0.0005   0.0168   1.0000
  13.250   0.8680   0.09557   0.09201  -0.0058   0.0169   1.0000
  13.500   0.8331   0.10976   0.10633  -0.0154   0.0173   1.0000
<< Back to NACA 65(1)-212 (naca651212-il)

Polar data table (+)

Polar graphs


<< Back to NACA 65(1)-212 (naca651212-il)