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NACA 0010-34 (naca001034-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 0010-34 (naca001034-il)
Reynolds number: 50,000
Max Cl/Cd: 25.07 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca001034-il-50000-n5.txt
Download as CSV file: xf-naca001034-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0010-34                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.6268   0.09892   0.09201  -0.0221   1.0000   0.0366
 -10.000  -0.6334   0.09270   0.08592  -0.0261   1.0000   0.0358
  -9.750  -0.6445   0.08691   0.08013  -0.0298   1.0000   0.0352
  -9.500  -0.6589   0.08181   0.07500  -0.0322   1.0000   0.0346
  -9.250  -0.6752   0.07747   0.07059  -0.0328   1.0000   0.0341
  -9.000  -0.6920   0.07371   0.06674  -0.0317   1.0000   0.0336
  -8.750  -0.7057   0.06984   0.06269  -0.0302   1.0000   0.0330
  -8.500  -0.7161   0.06597   0.05856  -0.0282   1.0000   0.0323
  -8.250  -0.7237   0.06220   0.05442  -0.0257   1.0000   0.0316
  -7.750  -0.7245   0.05576   0.04705  -0.0200   1.0000   0.0306
  -7.500  -0.7190   0.05235   0.04331  -0.0176   1.0000   0.0305
  -7.250  -0.7115   0.04913   0.03960  -0.0151   1.0000   0.0305
  -7.000  -0.7025   0.04582   0.03598  -0.0127   1.0000   0.0311
  -6.750  -0.6902   0.04294   0.03295  -0.0110   1.0000   0.0327
  -6.500  -0.6756   0.04042   0.03009  -0.0090   1.0000   0.0345
  -6.250  -0.6578   0.03785   0.02712  -0.0070   1.0000   0.0357
  -6.000  -0.6361   0.03532   0.02419  -0.0054   1.0000   0.0367
  -5.750  -0.6110   0.03302   0.02153  -0.0042   1.0000   0.0380
  -5.500  -0.5858   0.03091   0.01922  -0.0032   1.0000   0.0416
  -5.250  -0.5633   0.02925   0.01745  -0.0020   1.0000   0.0468
  -5.000  -0.5418   0.02779   0.01565  -0.0002   1.0000   0.0508
  -4.750  -0.5251   0.02628   0.01409   0.0018   1.0000   0.0586
  -4.500  -0.5087   0.02494   0.01263   0.0038   1.0000   0.0716
  -4.250  -0.4932   0.02329   0.01110   0.0059   1.0000   0.1005
  -4.000  -0.4961   0.01980   0.00994   0.0103   1.0000   0.4326
  -3.750  -0.4573   0.02138   0.01300   0.0180   1.0000   0.8392
  -3.500  -0.4190   0.02175   0.01278   0.0172   1.0000   0.8696
  -3.250  -0.3754   0.02187   0.01238   0.0146   1.0000   0.8885
  -3.000  -0.3325   0.02185   0.01193   0.0116   1.0000   0.9058
  -2.750  -0.2909   0.02174   0.01142   0.0085   1.0000   0.9220
  -2.500  -0.2502   0.02159   0.01096   0.0055   1.0000   0.9371
  -2.250  -0.2083   0.02139   0.01050   0.0020   1.0000   0.9508
  -2.000  -0.1664   0.02116   0.01001  -0.0016   1.0000   0.9638
  -1.750  -0.1246   0.02090   0.00957  -0.0053   1.0000   0.9763
  -1.500  -0.0813   0.02060   0.00911  -0.0095   1.0000   0.9875
  -1.250  -0.0379   0.02028   0.00868  -0.0137   1.0000   0.9981
  -1.000  -0.0238   0.02010   0.00847  -0.0123   1.0000   1.0000
  -0.750  -0.0169   0.01997   0.00833  -0.0094   1.0000   1.0000
  -0.500  -0.0108   0.01988   0.00822  -0.0064   1.0000   1.0000
  -0.250  -0.0052   0.01983   0.00816  -0.0032   1.0000   1.0000
   0.000   0.0000   0.01981   0.00814   0.0000   1.0000   1.0000
   0.250   0.0052   0.01983   0.00816   0.0032   1.0000   1.0000
   0.500   0.0108   0.01988   0.00822   0.0064   1.0000   1.0000
   0.750   0.0169   0.01997   0.00832   0.0095   1.0000   1.0000
   1.000   0.0238   0.02009   0.00846   0.0123   1.0000   1.0000
   1.250   0.0379   0.02028   0.00868   0.0137   0.9981   1.0000
   1.500   0.0813   0.02060   0.00911   0.0095   0.9875   1.0000
   1.750   0.1246   0.02090   0.00957   0.0053   0.9763   1.0000
   2.000   0.1664   0.02115   0.01000   0.0016   0.9638   1.0000
   2.250   0.2082   0.02138   0.01049  -0.0020   0.9509   1.0000
   2.500   0.2502   0.02158   0.01095  -0.0055   0.9371   1.0000
   2.750   0.2909   0.02174   0.01142  -0.0085   0.9221   1.0000
   3.000   0.3325   0.02184   0.01193  -0.0116   0.9059   1.0000
   3.250   0.3753   0.02186   0.01238  -0.0146   0.8885   1.0000
   3.500   0.4191   0.02175   0.01277  -0.0172   0.8697   1.0000
   3.750   0.4573   0.02138   0.01300  -0.0180   0.8392   1.0000
   4.000   0.4962   0.01979   0.00994  -0.0103   0.4342   1.0000
   4.250   0.4931   0.02329   0.01110  -0.0059   0.1005   1.0000
   4.500   0.5087   0.02493   0.01263  -0.0038   0.0717   1.0000
   4.750   0.5251   0.02628   0.01408  -0.0017   0.0586   1.0000
   5.000   0.5418   0.02779   0.01565   0.0002   0.0508   1.0000
   5.250   0.5632   0.02924   0.01744   0.0020   0.0468   1.0000
   5.500   0.5857   0.03090   0.01921   0.0032   0.0416   1.0000
   5.750   0.6109   0.03301   0.02152   0.0042   0.0380   1.0000
   6.000   0.6360   0.03532   0.02418   0.0054   0.0366   1.0000
   6.250   0.6578   0.03785   0.02711   0.0070   0.0357   1.0000
   6.500   0.6756   0.04041   0.03009   0.0090   0.0345   1.0000
   6.750   0.6902   0.04294   0.03294   0.0110   0.0327   1.0000
   7.000   0.7025   0.04583   0.03598   0.0127   0.0311   1.0000
   7.250   0.7115   0.04913   0.03960   0.0151   0.0305   1.0000
   7.500   0.7191   0.05235   0.04331   0.0176   0.0305   1.0000
   7.750   0.7245   0.05577   0.04706   0.0200   0.0306   1.0000
   8.250   0.7239   0.06221   0.05443   0.0257   0.0316   1.0000
   8.500   0.7162   0.06599   0.05858   0.0282   0.0323   1.0000
   8.750   0.7059   0.06987   0.06271   0.0302   0.0330   1.0000
   9.000   0.6923   0.07374   0.06677   0.0316   0.0336   1.0000
   9.250   0.6755   0.07751   0.07063   0.0327   0.0341   1.0000
   9.500   0.6593   0.08186   0.07505   0.0321   0.0346   1.0000
   9.750   0.6450   0.08698   0.08020   0.0297   0.0352   1.0000
  10.000   0.6340   0.09278   0.08600   0.0260   0.0359   1.0000
  10.250   0.6275   0.09900   0.09209   0.0219   0.0366   1.0000
  10.500   0.6242   0.10474   0.09780   0.0187   0.0375   1.0000
  10.750   0.6228   0.10987   0.10298   0.0165   0.0383   1.0000
  11.000   0.6243   0.11429   0.10737   0.0157   0.0393   1.0000
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