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NACA 0010-35 (naca001035-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 0010-35 (naca001035-il)
Reynolds number: 50,000
Max Cl/Cd: 18.75 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca001035-il-50000-n5.txt
Download as CSV file: xf-naca001035-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0010-35                                    
  
 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  -0.5833   0.11529   0.10814  -0.0280   1.0000   0.0599
 -10.500  -0.5859   0.10958   0.10247  -0.0307   1.0000   0.0494
 -10.250  -0.5905   0.10449   0.09744  -0.0329   1.0000   0.0468
 -10.000  -0.6006   0.09831   0.09134  -0.0372   1.0000   0.0445
  -9.750  -0.6225   0.09254   0.08558  -0.0412   1.0000   0.0428
  -9.500  -0.6306   0.08882   0.08181  -0.0409   1.0000   0.0405
  -9.250  -0.6414   0.08528   0.07828  -0.0395   1.0000   0.0398
  -9.000  -0.6562   0.08218   0.07518  -0.0370   1.0000   0.0392
  -8.750  -0.6718   0.07926   0.07224  -0.0338   1.0000   0.0386
  -8.500  -0.6847   0.07607   0.06899  -0.0308   1.0000   0.0379
  -8.250  -0.6964   0.07288   0.06570  -0.0275   1.0000   0.0371
  -8.000  -0.7065   0.06963   0.06230  -0.0240   1.0000   0.0363
  -7.750  -0.7150   0.06632   0.05880  -0.0202   1.0000   0.0354
  -7.500  -0.7218   0.06297   0.05517  -0.0161   1.0000   0.0344
  -7.250  -0.7263   0.05963   0.05144  -0.0117   1.0000   0.0333
  -6.750  -0.7236   0.05381   0.04471  -0.0035   1.0000   0.0319
  -6.500  -0.7179   0.05067   0.04124  -0.0001   1.0000   0.0317
  -6.250  -0.7099   0.04766   0.03784   0.0031   1.0000   0.0317
  -6.000  -0.6996   0.04502   0.03468   0.0065   1.0000   0.0321
  -5.750  -0.6875   0.04191   0.03146   0.0085   1.0000   0.0339
  -5.500  -0.6720   0.03953   0.02875   0.0107   1.0000   0.0360
  -5.250  -0.6522   0.03704   0.02582   0.0127   1.0000   0.0372
  -5.000  -0.6278   0.03459   0.02285   0.0141   1.0000   0.0383
  -4.750  -0.5992   0.03244   0.02026   0.0149   1.0000   0.0406
  -4.500  -0.5693   0.03036   0.01807   0.0148   1.0000   0.0467
  -4.250  -0.5366   0.02872   0.01612   0.0148   1.0000   0.0522
  -4.000  -0.5119   0.02731   0.01457   0.0155   1.0000   0.0630
  -3.750  -0.2884   0.02623   0.01624  -0.0117   1.0000   0.9585
  -3.500  -0.2417   0.02580   0.01523  -0.0163   1.0000   0.9731
  -3.250  -0.2005   0.02533   0.01433  -0.0201   1.0000   0.9843
  -3.000  -0.1602   0.02482   0.01348  -0.0238   1.0000   0.9939
  -2.750  -0.1279   0.02438   0.01273  -0.0259   1.0000   1.0000
  -2.500  -0.1160   0.02412   0.01233  -0.0237   1.0000   1.0000
  -2.250  -0.1042   0.02389   0.01198  -0.0215   1.0000   1.0000
  -2.000  -0.0924   0.02369   0.01167  -0.0193   1.0000   1.0000
  -1.750  -0.0807   0.02352   0.01138  -0.0170   1.0000   1.0000
  -1.500  -0.0691   0.02338   0.01115  -0.0146   1.0000   1.0000
  -1.250  -0.0575   0.02326   0.01096  -0.0122   1.0000   1.0000
  -1.000  -0.0459   0.02317   0.01081  -0.0098   1.0000   1.0000
  -0.750  -0.0344   0.02309   0.01070  -0.0074   1.0000   1.0000
  -0.500  -0.0229   0.02304   0.01061  -0.0049   1.0000   1.0000
  -0.250  -0.0115   0.02301   0.01056  -0.0025   1.0000   1.0000
   0.000   0.0000   0.02300   0.01054   0.0000   1.0000   1.0000
   0.250   0.0115   0.02301   0.01055   0.0025   1.0000   1.0000
   0.500   0.0229   0.02304   0.01060   0.0049   1.0000   1.0000
   0.750   0.0344   0.02309   0.01070   0.0074   1.0000   1.0000
   1.000   0.0459   0.02316   0.01081   0.0098   1.0000   1.0000
   1.250   0.0575   0.02326   0.01096   0.0122   1.0000   1.0000
   1.500   0.0691   0.02337   0.01115   0.0146   1.0000   1.0000
   1.750   0.0807   0.02352   0.01137   0.0170   1.0000   1.0000
   2.000   0.0924   0.02368   0.01166   0.0193   1.0000   1.0000
   2.250   0.1042   0.02388   0.01197   0.0215   1.0000   1.0000
   2.500   0.1161   0.02411   0.01232   0.0237   1.0000   1.0000
   2.750   0.1280   0.02437   0.01272   0.0259   1.0000   1.0000
   3.000   0.1601   0.02481   0.01347   0.0238   0.9940   1.0000
   3.250   0.2005   0.02531   0.01432   0.0201   0.9844   1.0000
   3.500   0.2416   0.02579   0.01522   0.0163   0.9732   1.0000
   3.750   0.2882   0.02621   0.01623   0.0117   0.9586   1.0000
   4.000   0.5119   0.02731   0.01456  -0.0155   0.0630   1.0000
   4.250   0.5366   0.02872   0.01612  -0.0147   0.0522   1.0000
   4.500   0.5693   0.03036   0.01807  -0.0148   0.0467   1.0000
   4.750   0.5991   0.03243   0.02026  -0.0149   0.0406   1.0000
   5.000   0.6277   0.03458   0.02284  -0.0141   0.0383   1.0000
   5.250   0.6521   0.03704   0.02582  -0.0127   0.0372   1.0000
   5.500   0.6720   0.03953   0.02875  -0.0107   0.0359   1.0000
   5.750   0.6875   0.04190   0.03145  -0.0085   0.0339   1.0000
   6.000   0.6996   0.04501   0.03467  -0.0065   0.0321   1.0000
   6.250   0.7099   0.04765   0.03784  -0.0031   0.0317   1.0000
   6.500   0.7178   0.05066   0.04123   0.0002   0.0317   1.0000
   6.750   0.7236   0.05380   0.04470   0.0035   0.0319   1.0000
   7.250   0.7263   0.05962   0.05143   0.0117   0.0333   1.0000
   7.500   0.7218   0.06296   0.05516   0.0161   0.0344   1.0000
   7.750   0.7150   0.06632   0.05880   0.0202   0.0354   1.0000
   8.000   0.7066   0.06962   0.06230   0.0240   0.0363   1.0000
   8.250   0.6965   0.07287   0.06569   0.0275   0.0371   1.0000
   8.500   0.6849   0.07607   0.06899   0.0308   0.0379   1.0000
   8.750   0.6719   0.07926   0.07224   0.0338   0.0386   1.0000
   9.000   0.6564   0.08219   0.07519   0.0370   0.0392   1.0000
   9.250   0.6417   0.08529   0.07829   0.0394   0.0398   1.0000
   9.500   0.6310   0.08883   0.08182   0.0408   0.0405   1.0000
   9.750   0.6226   0.09256   0.08561   0.0411   0.0429   1.0000
  10.000   0.6010   0.09837   0.09139   0.0370   0.0446   1.0000
  10.250   0.5910   0.10454   0.09749   0.0327   0.0468   1.0000
  10.500   0.5866   0.10962   0.10250   0.0306   0.0494   1.0000
  10.750   0.5839   0.11535   0.10820   0.0279   0.0601   1.0000
  11.000   0.4640   0.10868   0.10194   0.0338   0.0467   1.0000
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