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NACA 642-015 AIRFOIL (n64015-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 642-015 AIRFOIL (n64015-il)
Reynolds number: 100,000
Max Cl/Cd: 35.12 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n64015-il-100000-n5.txt
Download as CSV file: xf-n64015-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 642-015 AIRFOIL                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.000  -0.7981   0.10914   0.10360  -0.0125   1.0000   0.0334
 -14.750  -0.8282   0.09904   0.09334  -0.0190   1.0000   0.0332
 -14.500  -0.8565   0.09053   0.08465  -0.0242   1.0000   0.0331
 -14.250  -0.8809   0.08351   0.07744  -0.0280   1.0000   0.0329
 -14.000  -0.9043   0.07722   0.07092  -0.0310   1.0000   0.0329
 -13.750  -0.9233   0.07191   0.06538  -0.0330   1.0000   0.0329
 -13.500  -0.9404   0.06715   0.06036  -0.0343   1.0000   0.0330
 -13.250  -0.9554   0.06285   0.05578  -0.0350   1.0000   0.0331
 -13.000  -0.9660   0.05914   0.05181  -0.0351   1.0000   0.0332
 -12.750  -0.9758   0.05568   0.04803  -0.0348   1.0000   0.0334
 -12.500  -0.9755   0.05277   0.04494  -0.0344   1.0000   0.0338
 -12.250  -0.9700   0.05030   0.04233  -0.0339   1.0000   0.0342
 -12.000  -0.9634   0.04812   0.04003  -0.0333   1.0000   0.0347
 -11.750  -0.9564   0.04624   0.03806  -0.0327   1.0000   0.0356
 -11.500  -0.9480   0.04433   0.03600  -0.0319   1.0000   0.0365
 -11.250  -0.9382   0.04250   0.03399  -0.0311   1.0000   0.0377
 -11.000  -0.9249   0.04063   0.03191  -0.0303   1.0000   0.0388
 -10.750  -0.9083   0.03884   0.02986  -0.0297   1.0000   0.0399
 -10.500  -0.8877   0.03717   0.02804  -0.0292   1.0000   0.0409
 -10.250  -0.8673   0.03568   0.02659  -0.0289   1.0000   0.0422
 -10.000  -0.8498   0.03441   0.02531  -0.0284   1.0000   0.0438
  -9.750  -0.8322   0.03321   0.02403  -0.0277   1.0000   0.0459
  -9.500  -0.8133   0.03207   0.02276  -0.0270   1.0000   0.0480
  -9.250  -0.7961   0.03083   0.02153  -0.0263   1.0000   0.0502
  -9.000  -0.7812   0.02970   0.02044  -0.0253   1.0000   0.0522
  -8.750  -0.7667   0.02867   0.01939  -0.0243   1.0000   0.0551
  -8.500  -0.7520   0.02773   0.01837  -0.0231   1.0000   0.0585
  -8.250  -0.7426   0.02664   0.01736  -0.0215   1.0000   0.0615
  -8.000  -0.7328   0.02577   0.01649  -0.0197   1.0000   0.0651
  -7.750  -0.7236   0.02500   0.01570  -0.0176   1.0000   0.0696
  -7.500  -0.7147   0.02412   0.01490  -0.0158   0.9913   0.0751
  -7.250  -0.6873   0.02303   0.01381  -0.0174   0.9694   0.0859
  -7.000  -0.6611   0.02194   0.01278  -0.0187   0.9529   0.1040
  -6.750  -0.6397   0.02081   0.01182  -0.0190   0.9373   0.1361
  -6.500  -0.6248   0.01959   0.01090  -0.0181   0.9216   0.1915
  -6.250  -0.6159   0.01827   0.01006  -0.0162   0.9064   0.2775
  -6.000  -0.6072   0.01729   0.00976  -0.0135   0.8928   0.3879
  -5.750  -0.5885   0.01712   0.00978  -0.0117   0.8817   0.4655
  -5.500  -0.5674   0.01712   0.00974  -0.0102   0.8713   0.5052
  -5.250  -0.5454   0.01722   0.00980  -0.0089   0.8609   0.5355
  -5.000  -0.5227   0.01735   0.00982  -0.0075   0.8522   0.5601
  -4.750  -0.4986   0.01756   0.00999  -0.0063   0.8425   0.5797
  -4.500  -0.4741   0.01782   0.01018  -0.0051   0.8343   0.5978
  -4.250  -0.4493   0.01807   0.01038  -0.0040   0.8255   0.6138
  -4.000  -0.4246   0.01815   0.01036  -0.0030   0.8178   0.6261
  -3.750  -0.3983   0.01818   0.01029  -0.0025   0.8095   0.6341
  -3.500  -0.3732   0.01801   0.00998  -0.0021   0.8026   0.6409
  -3.250  -0.3462   0.01797   0.00988  -0.0019   0.7944   0.6456
  -3.000  -0.3205   0.01784   0.00960  -0.0014   0.7882   0.6517
  -2.750  -0.2946   0.01772   0.00940  -0.0013   0.7799   0.6577
  -2.500  -0.2677   0.01767   0.00929  -0.0009   0.7734   0.6624
  -2.250  -0.2415   0.01757   0.00910  -0.0008   0.7665   0.6682
  -2.000  -0.2153   0.01744   0.00888  -0.0007   0.7598   0.6735
  -1.750  -0.1881   0.01738   0.00877  -0.0004   0.7548   0.6774
  -1.500  -0.1613   0.01733   0.00869  -0.0004   0.7473   0.6825
  -1.250  -0.1352   0.01720   0.00846  -0.0004   0.7413   0.6887
  -1.000  -0.1078   0.01717   0.00842  -0.0002   0.7357   0.6923
  -0.750  -0.0808   0.01715   0.00840  -0.0002   0.7290   0.6969
  -0.500  -0.0541   0.01708   0.00827  -0.0001   0.7240   0.7029
  -0.250  -0.0270   0.01708   0.00826  -0.0001   0.7189   0.7079
   0.000   0.0000   0.01712   0.00833   0.0000   0.7128   0.7128
   0.250   0.0269   0.01708   0.00826   0.0001   0.7079   0.7190
   0.500   0.0540   0.01708   0.00827   0.0001   0.7029   0.7240
   0.750   0.0808   0.01715   0.00840   0.0002   0.6969   0.7290
   1.000   0.1078   0.01717   0.00842   0.0002   0.6923   0.7357
   1.250   0.1351   0.01720   0.00846   0.0004   0.6887   0.7413
   1.500   0.1613   0.01733   0.00869   0.0004   0.6825   0.7473
   1.750   0.1881   0.01738   0.00877   0.0004   0.6774   0.7548
   2.000   0.2152   0.01744   0.00888   0.0007   0.6735   0.7598
   2.250   0.2415   0.01757   0.00910   0.0008   0.6682   0.7665
   2.500   0.2677   0.01767   0.00929   0.0009   0.6624   0.7734
   2.750   0.2946   0.01772   0.00940   0.0013   0.6577   0.7799
   3.000   0.3205   0.01784   0.00960   0.0014   0.6517   0.7882
   3.250   0.3461   0.01797   0.00988   0.0019   0.6456   0.7944
   3.500   0.3732   0.01801   0.00998   0.0021   0.6410   0.8026
   3.750   0.3983   0.01818   0.01029   0.0025   0.6342   0.8095
   4.000   0.4246   0.01815   0.01036   0.0030   0.6261   0.8178
   4.250   0.4493   0.01807   0.01038   0.0039   0.6138   0.8255
   4.500   0.4742   0.01782   0.01018   0.0051   0.5979   0.8343
   4.750   0.4986   0.01756   0.00999   0.0063   0.5797   0.8425
   5.000   0.5228   0.01734   0.00982   0.0075   0.5601   0.8522
   5.250   0.5454   0.01722   0.00980   0.0088   0.5356   0.8609
   5.500   0.5674   0.01712   0.00974   0.0102   0.5052   0.8713
   5.750   0.5885   0.01712   0.00977   0.0117   0.4654   0.8818
   6.000   0.6073   0.01729   0.00976   0.0134   0.3885   0.8928
   6.250   0.6160   0.01826   0.01005   0.0161   0.2778   0.9064
   6.500   0.6250   0.01959   0.01090   0.0181   0.1914   0.9216
   6.750   0.6399   0.02081   0.01182   0.0189   0.1361   0.9373
   7.000   0.6614   0.02194   0.01278   0.0186   0.1039   0.9529
   7.250   0.6875   0.02303   0.01381   0.0174   0.0859   0.9694
   7.500   0.7150   0.02412   0.01490   0.0158   0.0751   0.9916
   7.750   0.7238   0.02500   0.01570   0.0176   0.0695   1.0000
   8.000   0.7333   0.02577   0.01649   0.0196   0.0649   1.0000
   8.250   0.7431   0.02664   0.01736   0.0214   0.0614   1.0000
   8.500   0.7524   0.02775   0.01837   0.0231   0.0583   1.0000
   8.750   0.7673   0.02867   0.01939   0.0242   0.0550   1.0000
   9.000   0.7819   0.02970   0.02044   0.0252   0.0522   1.0000
   9.250   0.7967   0.03085   0.02155   0.0262   0.0500   1.0000
   9.500   0.8143   0.03208   0.02277   0.0269   0.0481   1.0000
   9.750   0.8330   0.03323   0.02404   0.0276   0.0458   1.0000
  10.000   0.8507   0.03443   0.02532   0.0282   0.0437   1.0000
  10.250   0.8679   0.03569   0.02659   0.0288   0.0421   1.0000
  10.500   0.8886   0.03718   0.02805   0.0291   0.0409   1.0000
  10.750   0.9094   0.03887   0.02989   0.0295   0.0399   1.0000
  11.000   0.9258   0.04066   0.03194   0.0302   0.0388   1.0000
  11.250   0.9387   0.04250   0.03399   0.0309   0.0375   1.0000
  11.500   0.9492   0.04438   0.03605   0.0317   0.0365   1.0000
  11.750   0.9574   0.04625   0.03806   0.0325   0.0355   1.0000
  12.000   0.9647   0.04825   0.04019   0.0332   0.0349   1.0000
  12.250   0.9712   0.05033   0.04237   0.0337   0.0342   1.0000
  12.500   0.9764   0.05281   0.04499   0.0342   0.0338   1.0000
  12.750   0.9767   0.05575   0.04811   0.0346   0.0334   1.0000
  13.000   0.9679   0.05914   0.05180   0.0349   0.0332   1.0000
  13.250   0.9561   0.06296   0.05590   0.0348   0.0331   1.0000
  13.500   0.9423   0.06715   0.06036   0.0341   0.0330   1.0000
  13.750   0.9252   0.07193   0.06540   0.0328   0.0329   1.0000
  14.000   0.9045   0.07745   0.07115   0.0307   0.0329   1.0000
  14.250   0.8819   0.08365   0.07759   0.0277   0.0329   1.0000
  14.500   0.8576   0.09068   0.08482   0.0238   0.0331   1.0000
  14.750   0.8295   0.09918   0.09349   0.0186   0.0332   1.0000
  15.000   0.8007   0.10903   0.10350   0.0123   0.0334   1.0000
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