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NACA 0010 (naca0010-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 0010 (naca0010-il)
Reynolds number: 50,000
Max Cl/Cd: 25.72 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca0010-il-50000-n5.txt
Download as CSV file: xf-naca0010-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0010                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.8297   0.07541   0.06782  -0.0232   1.0000   0.0595
 -10.500  -0.8517   0.07046   0.06270  -0.0240   1.0000   0.0595
 -10.250  -0.8713   0.06587   0.05785  -0.0235   1.0000   0.0596
 -10.000  -0.8721   0.06242   0.05434  -0.0228   1.0000   0.0608
  -9.750  -0.8666   0.05990   0.05175  -0.0220   1.0000   0.0629
  -9.500  -0.8659   0.05668   0.04829  -0.0211   1.0000   0.0649
  -9.250  -0.8657   0.05301   0.04425  -0.0199   1.0000   0.0668
  -9.000  -0.8623   0.04925   0.04002  -0.0186   1.0000   0.0684
  -8.750  -0.8549   0.04575   0.03595  -0.0172   1.0000   0.0704
  -8.500  -0.8423   0.04300   0.03286  -0.0160   1.0000   0.0735
  -8.250  -0.8250   0.04102   0.03076  -0.0151   1.0000   0.0771
  -8.000  -0.8070   0.03866   0.02807  -0.0141   1.0000   0.0801
  -7.750  -0.7872   0.03639   0.02534  -0.0131   1.0000   0.0834
  -7.500  -0.7667   0.03458   0.02341  -0.0123   1.0000   0.0881
  -7.250  -0.7454   0.03305   0.02176  -0.0114   1.0000   0.0935
  -7.000  -0.7219   0.03138   0.01975  -0.0105   1.0000   0.0985
  -6.750  -0.6997   0.02989   0.01831  -0.0096   1.0000   0.1037
  -6.500  -0.6771   0.02859   0.01681  -0.0087   1.0000   0.1120
  -6.250  -0.6563   0.02738   0.01565  -0.0077   1.0000   0.1232
  -6.000  -0.6352   0.02617   0.01445  -0.0066   1.0000   0.1372
  -5.750  -0.6141   0.02497   0.01327  -0.0056   1.0000   0.1563
  -5.500  -0.5940   0.02382   0.01224  -0.0046   1.0000   0.1856
  -5.250  -0.5744   0.02272   0.01140  -0.0035   1.0000   0.2264
  -5.000  -0.5553   0.02172   0.01071  -0.0023   1.0000   0.2809
  -4.750  -0.5365   0.02086   0.01016  -0.0009   1.0000   0.3432
  -4.500  -0.5174   0.02016   0.00969   0.0007   1.0000   0.4043
  -4.250  -0.4984   0.01959   0.00932   0.0026   1.0000   0.4613
  -4.000  -0.4792   0.01912   0.00903   0.0045   1.0000   0.5163
  -3.750  -0.4595   0.01872   0.00881   0.0066   1.0000   0.5689
  -3.500  -0.4392   0.01840   0.00862   0.0088   1.0000   0.6193
  -3.250  -0.4182   0.01816   0.00849   0.0109   1.0000   0.6669
  -3.000  -0.3959   0.01799   0.00840   0.0130   1.0000   0.7117
  -2.750  -0.3721   0.01790   0.00833   0.0147   1.0000   0.7542
  -2.500  -0.3464   0.01786   0.00828   0.0161   1.0000   0.7953
  -2.250  -0.3153   0.01789   0.00828   0.0164   1.0000   0.8324
  -2.000  -0.2812   0.01794   0.00824   0.0159   1.0000   0.8677
  -1.750  -0.2421   0.01800   0.00819   0.0142   1.0000   0.8996
  -1.500  -0.1958   0.01804   0.00810   0.0108   1.0000   0.9266
  -1.250  -0.1450   0.01803   0.00797   0.0062   1.0000   0.9505
  -1.000  -0.0925   0.01794   0.00777   0.0009   1.0000   0.9724
  -0.750  -0.0386   0.01776   0.00752  -0.0049   1.0000   0.9917
  -0.500  -0.0110   0.01757   0.00732  -0.0060   1.0000   1.0000
  -0.250  -0.0053   0.01745   0.00721  -0.0031   1.0000   1.0000
   0.000   0.0000   0.01742   0.00718   0.0000   1.0000   1.0000
   0.250   0.0053   0.01745   0.00721   0.0031   1.0000   1.0000
   0.500   0.0110   0.01757   0.00731   0.0060   1.0000   1.0000
   0.750   0.0386   0.01776   0.00752   0.0049   0.9917   1.0000
   1.000   0.0925   0.01794   0.00777  -0.0009   0.9724   1.0000
   1.250   0.1450   0.01803   0.00796  -0.0062   0.9505   1.0000
   1.500   0.1958   0.01804   0.00810  -0.0108   0.9266   1.0000
   1.750   0.2420   0.01800   0.00819  -0.0142   0.8996   1.0000
   2.000   0.2811   0.01794   0.00824  -0.0159   0.8677   1.0000
   2.250   0.3153   0.01789   0.00828  -0.0164   0.8324   1.0000
   2.500   0.3463   0.01786   0.00828  -0.0161   0.7953   1.0000
   2.750   0.3720   0.01790   0.00833  -0.0147   0.7542   1.0000
   3.000   0.3959   0.01799   0.00840  -0.0130   0.7117   1.0000
   3.250   0.4181   0.01816   0.00849  -0.0109   0.6669   1.0000
   3.500   0.4392   0.01840   0.00862  -0.0088   0.6193   1.0000
   3.750   0.4594   0.01872   0.00881  -0.0066   0.5689   1.0000
   4.000   0.4791   0.01912   0.00903  -0.0045   0.5163   1.0000
   4.250   0.4984   0.01959   0.00932  -0.0025   0.4614   1.0000
   4.500   0.5173   0.02016   0.00969  -0.0007   0.4043   1.0000
   4.750   0.5365   0.02086   0.01016   0.0009   0.3432   1.0000
   5.000   0.5553   0.02172   0.01071   0.0023   0.2809   1.0000
   5.250   0.5744   0.02271   0.01140   0.0035   0.2264   1.0000
   5.500   0.5940   0.02382   0.01224   0.0046   0.1856   1.0000
   5.750   0.6141   0.02497   0.01327   0.0056   0.1563   1.0000
   6.000   0.6352   0.02617   0.01445   0.0066   0.1372   1.0000
   6.250   0.6563   0.02738   0.01565   0.0077   0.1232   1.0000
   6.500   0.6772   0.02859   0.01681   0.0087   0.1120   1.0000
   6.750   0.6998   0.02989   0.01831   0.0096   0.1037   1.0000
   7.000   0.7219   0.03138   0.01975   0.0105   0.0985   1.0000
   7.250   0.7454   0.03305   0.02175   0.0114   0.0935   1.0000
   7.500   0.7667   0.03458   0.02340   0.0123   0.0880   1.0000
   7.750   0.7872   0.03638   0.02534   0.0131   0.0834   1.0000
   8.000   0.8071   0.03866   0.02807   0.0141   0.0801   1.0000
   8.250   0.8251   0.04102   0.03076   0.0151   0.0771   1.0000
   8.500   0.8424   0.04300   0.03286   0.0160   0.0735   1.0000
   8.750   0.8550   0.04575   0.03596   0.0172   0.0704   1.0000
   9.000   0.8624   0.04926   0.04002   0.0186   0.0684   1.0000
   9.250   0.8659   0.05301   0.04425   0.0199   0.0668   1.0000
   9.500   0.8661   0.05668   0.04830   0.0210   0.0649   1.0000
   9.750   0.8669   0.05990   0.05175   0.0220   0.0629   1.0000
  10.000   0.8725   0.06241   0.05432   0.0228   0.0608   1.0000
  10.250   0.8714   0.06590   0.05788   0.0234   0.0596   1.0000
  10.500   0.8519   0.07050   0.06274   0.0239   0.0595   1.0000
  10.750   0.8299   0.07546   0.06787   0.0231   0.0595   1.0000
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