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NACA 0010-34 (naca001034-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 0010-34 (naca001034-il)
Reynolds number: 500,000
Max Cl/Cd: 43.86 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca001034-il-500000-n5.txt
Download as CSV file: xf-naca001034-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.6635   0.07781   0.07566  -0.0268   1.0000   0.0035
 -10.000  -0.6772   0.07025   0.06801  -0.0327   1.0000   0.0035
  -9.750  -0.6915   0.06497   0.06263  -0.0352   1.0000   0.0034
  -9.500  -0.7048   0.06089   0.05844  -0.0354   1.0000   0.0034
  -9.250  -0.7167   0.05760   0.05503  -0.0337   1.0000   0.0033
  -9.000  -0.7261   0.05474   0.05205  -0.0310   1.0000   0.0033
  -8.750  -0.7294   0.05180   0.04898  -0.0286   1.0000   0.0033
  -8.500  -0.7306   0.04903   0.04605  -0.0260   1.0000   0.0032
  -8.250  -0.7304   0.04645   0.04333  -0.0231   1.0000   0.0032
  -8.000  -0.7334   0.04362   0.04030  -0.0195   1.0000   0.0031
  -7.750  -0.7440   0.03944   0.03584  -0.0144   1.0000   0.0030
  -7.500  -0.7486   0.03583   0.03195  -0.0095   1.0000   0.0029
  -7.250  -0.7458   0.03202   0.02778  -0.0058   0.9993   0.0029
  -7.000  -0.7279   0.02760   0.02288  -0.0047   0.9966   0.0029
  -6.750  -0.7060   0.02387   0.01868  -0.0041   0.9946   0.0028
  -6.500  -0.6826   0.02092   0.01532  -0.0033   0.9920   0.0028
  -6.250  -0.6568   0.01857   0.01263  -0.0031   0.9899   0.0029
  -6.000  -0.6298   0.01673   0.01054  -0.0031   0.9880   0.0029
  -5.750  -0.6020   0.01530   0.00884  -0.0034   0.9863   0.0030
  -5.500  -0.5780   0.01389   0.00725  -0.0029   0.9829   0.0033
  -5.250  -0.5525   0.01261   0.00579  -0.0027   0.9798   0.0048
  -5.000  -0.5216   0.01212   0.00526  -0.0036   0.9778   0.0074
  -4.750  -0.4899   0.01178   0.00491  -0.0049   0.9761   0.0105
  -4.500  -0.4622   0.01158   0.00472  -0.0052   0.9718   0.0150
  -4.250  -0.4324   0.01131   0.00439  -0.0059   0.9684   0.0173
  -4.000  -0.4027   0.01079   0.00380  -0.0066   0.9656   0.0212
  -3.750  -0.3752   0.01052   0.00347  -0.0067   0.9610   0.0235
  -3.500  -0.3467   0.01028   0.00313  -0.0070   0.9564   0.0267
  -3.250  -0.3178   0.00990   0.00284  -0.0075   0.9527   0.0510
  -3.000  -0.2988   0.00881   0.00242  -0.0064   0.9455   0.2206
  -2.750  -0.2779   0.00781   0.00210  -0.0056   0.9398   0.3917
  -2.500  -0.2570   0.00717   0.00190  -0.0046   0.9325   0.5041
  -2.250  -0.2343   0.00666   0.00175  -0.0037   0.9263   0.5988
  -2.000  -0.2105   0.00640   0.00166  -0.0029   0.9186   0.6517
  -1.750  -0.1847   0.00620   0.00157  -0.0024   0.9121   0.6936
  -1.500  -0.1610   0.00599   0.00151  -0.0015   0.9032   0.7463
  -1.250  -0.1358   0.00587   0.00150  -0.0008   0.8948   0.7844
  -1.000  -0.1087   0.00581   0.00145  -0.0006   0.8860   0.8000
  -0.750  -0.0817   0.00578   0.00142  -0.0004   0.8764   0.8134
  -0.500  -0.0545   0.00575   0.00139  -0.0002   0.8673   0.8256
  -0.250  -0.0272   0.00574   0.00137  -0.0001   0.8579   0.8368
   0.000   0.0000   0.00573   0.00136   0.0000   0.8476   0.8476
   0.250   0.0272   0.00574   0.00137   0.0001   0.8368   0.8579
   0.500   0.0545   0.00575   0.00139   0.0002   0.8255   0.8673
   0.750   0.0817   0.00578   0.00142   0.0004   0.8134   0.8765
   1.000   0.1087   0.00581   0.00145   0.0006   0.8001   0.8860
   1.250   0.1358   0.00587   0.00150   0.0008   0.7844   0.8948
   1.500   0.1610   0.00599   0.00151   0.0015   0.7459   0.9033
   1.750   0.1846   0.00620   0.00157   0.0024   0.6930   0.9121
   2.000   0.2105   0.00640   0.00166   0.0029   0.6524   0.9186
   2.250   0.2343   0.00666   0.00175   0.0037   0.5995   0.9263
   2.500   0.2569   0.00718   0.00190   0.0046   0.5030   0.9325
   2.750   0.2779   0.00780   0.00210   0.0056   0.3925   0.9398
   3.000   0.2988   0.00880   0.00242   0.0064   0.2213   0.9456
   3.250   0.3178   0.00990   0.00284   0.0075   0.0510   0.9528
   3.500   0.3467   0.01028   0.00312   0.0070   0.0267   0.9564
   3.750   0.3752   0.01052   0.00347   0.0067   0.0234   0.9610
   4.000   0.4027   0.01079   0.00380   0.0066   0.0211   0.9656
   4.250   0.4324   0.01131   0.00439   0.0059   0.0173   0.9685
   4.500   0.4622   0.01158   0.00471   0.0052   0.0150   0.9718
   4.750   0.4899   0.01178   0.00490   0.0049   0.0105   0.9761
   5.000   0.5217   0.01212   0.00526   0.0036   0.0074   0.9778
   5.250   0.5526   0.01260   0.00579   0.0026   0.0048   0.9798
   5.500   0.5783   0.01385   0.00721   0.0028   0.0033   0.9830
   5.750   0.6022   0.01530   0.00884   0.0033   0.0030   0.9864
   6.000   0.6300   0.01673   0.01054   0.0030   0.0029   0.9880
   6.250   0.6570   0.01859   0.01266   0.0030   0.0029   0.9899
   6.500   0.6828   0.02093   0.01533   0.0033   0.0028   0.9921
   6.750   0.7061   0.02388   0.01869   0.0041   0.0028   0.9946
   7.000   0.7280   0.02761   0.02289   0.0047   0.0029   0.9966
   7.250   0.7460   0.03204   0.02780   0.0057   0.0029   0.9993
   7.500   0.7485   0.03583   0.03195   0.0096   0.0029   1.0000
   7.750   0.7440   0.03944   0.03584   0.0144   0.0030   1.0000
   8.000   0.7334   0.04363   0.04031   0.0195   0.0031   1.0000
   8.250   0.7305   0.04646   0.04333   0.0231   0.0032   1.0000
   8.500   0.7307   0.04904   0.04607   0.0260   0.0032   1.0000
   8.750   0.7297   0.05181   0.04899   0.0286   0.0033   1.0000
   9.000   0.7265   0.05475   0.05207   0.0309   0.0033   1.0000
   9.250   0.7171   0.05764   0.05507   0.0336   0.0033   1.0000
   9.500   0.7054   0.06093   0.05848   0.0353   0.0034   1.0000
   9.750   0.6920   0.06504   0.06270   0.0351   0.0034   1.0000
  10.000   0.6778   0.07032   0.06808   0.0326   0.0035   1.0000
  10.250   0.6642   0.07797   0.07583   0.0265   0.0035   1.0000
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