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NACA 65(1)-412 (naca651412-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 65(1)-412 (naca651412-il)
Reynolds number: 500,000
Max Cl/Cd: 88.84 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca651412-il-500000-n5.txt
Download as CSV file: xf-naca651412-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(1)-412                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4891   0.08523   0.08289  -0.0518   1.0000   0.0096
 -10.750  -0.5131   0.07544   0.07316  -0.0576   1.0000   0.0097
 -10.500  -0.5940   0.05591   0.05351  -0.0711   1.0000   0.0092
 -10.250  -0.6281   0.04660   0.04389  -0.0770   0.9807   0.0094
 -10.000  -0.6801   0.02732   0.02307  -0.0814   0.9557   0.0106
  -9.750  -0.6622   0.02413   0.01935  -0.0820   0.9462   0.0111
  -9.500  -0.6395   0.02287   0.01793  -0.0825   0.9370   0.0116
  -9.250  -0.6159   0.02221   0.01716  -0.0826   0.9277   0.0118
  -9.000  -0.5915   0.02176   0.01663  -0.0827   0.9193   0.0122
  -8.750  -0.5697   0.02096   0.01567  -0.0823   0.9099   0.0127
  -8.500  -0.5480   0.01988   0.01438  -0.0818   0.9015   0.0132
  -8.250  -0.5261   0.01877   0.01305  -0.0812   0.8930   0.0137
  -8.000  -0.5033   0.01787   0.01196  -0.0807   0.8854   0.0143
  -7.750  -0.4796   0.01718   0.01109  -0.0803   0.8774   0.0147
  -7.500  -0.4570   0.01630   0.01011  -0.0799   0.8699   0.0154
  -7.250  -0.4325   0.01586   0.00962  -0.0796   0.8625   0.0159
  -7.000  -0.4079   0.01536   0.00903  -0.0794   0.8556   0.0165
  -6.750  -0.3835   0.01480   0.00838  -0.0790   0.8484   0.0170
  -6.500  -0.3588   0.01428   0.00776  -0.0787   0.8416   0.0177
  -6.250  -0.3338   0.01381   0.00719  -0.0784   0.8345   0.0184
  -6.000  -0.3083   0.01345   0.00673  -0.0782   0.8284   0.0190
  -5.750  -0.2840   0.01283   0.00605  -0.0779   0.8218   0.0197
  -5.500  -0.2592   0.01233   0.00549  -0.0776   0.8156   0.0205
  -5.250  -0.2335   0.01195   0.00508  -0.0775   0.8093   0.0213
  -5.000  -0.2075   0.01163   0.00469  -0.0774   0.8029   0.0221
  -4.750  -0.1813   0.01132   0.00432  -0.0773   0.7972   0.0231
  -4.500  -0.1546   0.01106   0.00402  -0.0773   0.7913   0.0244
  -4.250  -0.1278   0.01084   0.00373  -0.0773   0.7858   0.0253
  -4.000  -0.1014   0.01045   0.00329  -0.0773   0.7802   0.0271
  -3.750  -0.0744   0.01020   0.00302  -0.0773   0.7742   0.0290
  -3.500  -0.0471   0.01002   0.00278  -0.0774   0.7690   0.0312
  -3.250  -0.0195   0.00986   0.00258  -0.0775   0.7634   0.0336
  -3.000   0.0079   0.00965   0.00236  -0.0776   0.7582   0.0402
  -2.750   0.0355   0.00946   0.00219  -0.0777   0.7534   0.0518
  -2.500   0.0627   0.00910   0.00201  -0.0779   0.7480   0.1063
  -2.250   0.0888   0.00836   0.00177  -0.0784   0.7427   0.2579
  -2.000   0.1145   0.00737   0.00154  -0.0790   0.7381   0.4857
  -1.750   0.1417   0.00705   0.00159  -0.0791   0.7331   0.5992
  -1.500   0.1693   0.00700   0.00165  -0.0791   0.7282   0.6478
  -1.250   0.1975   0.00702   0.00166  -0.0792   0.7237   0.6666
  -1.000   0.2257   0.00702   0.00168  -0.0793   0.7189   0.6813
  -0.750   0.2541   0.00703   0.00167  -0.0794   0.7142   0.6880
  -0.250   0.3112   0.00708   0.00166  -0.0799   0.7053   0.6980
   0.000   0.3396   0.00709   0.00167  -0.0801   0.7006   0.7024
   0.250   0.3679   0.00712   0.00169  -0.0802   0.6963   0.7074
   0.500   0.3964   0.00715   0.00171  -0.0805   0.6920   0.7125
   0.750   0.4248   0.00717   0.00175  -0.0807   0.6874   0.7173
   1.000   0.4531   0.00721   0.00180  -0.0808   0.6831   0.7222
   1.250   0.4814   0.00726   0.00184  -0.0810   0.6791   0.7275
   1.500   0.5098   0.00728   0.00192  -0.0812   0.6746   0.7324
   1.750   0.5380   0.00732   0.00199  -0.0813   0.6700   0.7377
   2.250   0.5938   0.00742   0.00214  -0.0815   0.6563   0.7482
   2.500   0.6206   0.00747   0.00219  -0.0813   0.6422   0.7539
   2.750   0.6475   0.00755   0.00226  -0.0812   0.6273   0.7600
   3.000   0.6731   0.00766   0.00233  -0.0808   0.6047   0.7654
   3.250   0.6974   0.00785   0.00242  -0.0801   0.5653   0.7714
   3.500   0.7201   0.00818   0.00256  -0.0792   0.5117   0.7774
   3.750   0.7345   0.00914   0.00296  -0.0771   0.3891   0.7841
   4.250   0.7649   0.01125   0.00409  -0.0734   0.1714   0.7982
   4.500   0.7820   0.01214   0.00462  -0.0720   0.0922   0.8057
   4.750   0.8016   0.01276   0.00506  -0.0708   0.0501   0.8125
   5.000   0.8239   0.01319   0.00544  -0.0700   0.0365   0.8203
   5.250   0.8468   0.01351   0.00580  -0.0692   0.0312   0.8279
   5.500   0.8690   0.01390   0.00620  -0.0684   0.0267   0.8364
   5.750   0.8913   0.01421   0.00658  -0.0676   0.0244   0.8444
   6.000   0.9133   0.01456   0.00699  -0.0667   0.0223   0.8530
   6.250   0.9335   0.01498   0.00745  -0.0655   0.0204   0.8622
   6.500   0.9528   0.01543   0.00796  -0.0641   0.0190   0.8723
   6.750   0.9724   0.01582   0.00843  -0.0628   0.0181   0.8834
   7.000   0.9907   0.01624   0.00893  -0.0612   0.0172   0.8957
   7.250   1.0075   0.01666   0.00943  -0.0594   0.0164   0.9094
   8.000   1.0481   0.01839   0.01135  -0.0526   0.0146   1.0000
   8.250   1.0645   0.01905   0.01208  -0.0512   0.0144   1.0000
   8.500   1.0807   0.01975   0.01284  -0.0497   0.0140   1.0000
   8.750   1.0963   0.02048   0.01363  -0.0482   0.0137   1.0000
   9.000   1.1117   0.02125   0.01446  -0.0468   0.0133   1.0000
   9.250   1.1264   0.02209   0.01536  -0.0453   0.0129   1.0000
   9.500   1.1408   0.02298   0.01631  -0.0439   0.0126   1.0000
   9.750   1.1551   0.02389   0.01730  -0.0425   0.0124   1.0000
  10.000   1.1691   0.02486   0.01833  -0.0411   0.0121   1.0000
  10.250   1.1829   0.02587   0.01941  -0.0398   0.0119   1.0000
  10.500   1.1964   0.02691   0.02051  -0.0385   0.0117   1.0000
  10.750   1.2091   0.02807   0.02174  -0.0372   0.0115   1.0000
  11.000   1.2213   0.02935   0.02310  -0.0359   0.0113   1.0000
  11.250   1.2322   0.03086   0.02471  -0.0346   0.0111   1.0000
  11.500   1.2430   0.03250   0.02647  -0.0333   0.0109   1.0000
  11.750   1.2550   0.03384   0.02794  -0.0322   0.0107   1.0000
  12.000   1.2659   0.03529   0.02953  -0.0311   0.0105   1.0000
  12.250   1.2757   0.03689   0.03128  -0.0300   0.0103   1.0000
  12.500   1.2841   0.03866   0.03321  -0.0288   0.0101   1.0000
  12.750   1.2911   0.04060   0.03530  -0.0277   0.0100   1.0000
  13.000   1.2964   0.04270   0.03757  -0.0267   0.0098   1.0000
  13.250   1.2996   0.04508   0.04013  -0.0257   0.0096   1.0000
  13.500   1.3014   0.04756   0.04280  -0.0248   0.0095   1.0000
  13.750   1.3013   0.05032   0.04574  -0.0241   0.0094   1.0000
  14.000   1.2994   0.05330   0.04890  -0.0235   0.0092   1.0000
  14.250   1.2968   0.05638   0.05214  -0.0232   0.0091   1.0000
  14.500   1.2934   0.05966   0.05557  -0.0233   0.0090   1.0000
  14.750   1.2884   0.06325   0.05932  -0.0236   0.0089   1.0000
  15.000   1.2822   0.06717   0.06339  -0.0242   0.0088   1.0000
  15.250   1.2765   0.07120   0.06756  -0.0252   0.0087   1.0000
  15.500   1.2703   0.07549   0.07198  -0.0265   0.0086   1.0000
  15.750   1.2603   0.08066   0.07730  -0.0284   0.0085   1.0000
  16.000   1.2473   0.08665   0.08347  -0.0310   0.0085   1.0000
  16.250   1.2345   0.09299   0.08996  -0.0340   0.0084   1.0000
  16.500   1.2183   0.10040   0.09753  -0.0380   0.0084   1.0000
  16.750   1.1873   0.11173   0.10914  -0.0446   0.0084   1.0000
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