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NACA 2410 (naca2410-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 2410 (naca2410-il)
Reynolds number: 50,000
Max Cl/Cd: 35.35 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca2410-il-50000.txt
Download as CSV file: xf-naca2410-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2410                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4636   0.09537   0.08827  -0.0037   1.0000   0.3393
  -7.750  -0.4650   0.09272   0.08568  -0.0030   1.0000   0.3555
  -7.500  -0.4685   0.09019   0.08323  -0.0020   1.0000   0.3717
  -7.250  -0.4655   0.08709   0.08017  -0.0007   1.0000   0.3876
  -7.000  -0.4620   0.08399   0.07713   0.0007   1.0000   0.4033
  -6.500  -0.5338   0.05453   0.04680  -0.0382   1.0000   0.1719
  -6.250  -0.5216   0.05040   0.04250  -0.0377   1.0000   0.1701
  -6.000  -0.5089   0.04627   0.03810  -0.0374   1.0000   0.1674
  -5.750  -0.4951   0.04231   0.03371  -0.0371   1.0000   0.1665
  -5.500  -0.4794   0.03893   0.02974  -0.0367   1.0000   0.1699
  -5.250  -0.4609   0.03598   0.02637  -0.0360   1.0000   0.1732
  -5.000  -0.4403   0.03363   0.02382  -0.0351   1.0000   0.1768
  -4.750  -0.4184   0.03141   0.02120  -0.0343   1.0000   0.1822
  -4.500  -0.3965   0.02965   0.01923  -0.0335   1.0000   0.1924
  -4.250  -0.3733   0.02798   0.01728  -0.0328   1.0000   0.2046
  -4.000  -0.3492   0.02641   0.01553  -0.0320   1.0000   0.2187
  -3.750  -0.3260   0.02513   0.01433  -0.0311   1.0000   0.2413
  -3.500  -0.3023   0.02391   0.01313  -0.0303   1.0000   0.2753
  -3.250  -0.2789   0.02274   0.01213  -0.0294   1.0000   0.3254
  -3.000  -0.2564   0.02157   0.01139  -0.0282   1.0000   0.3941
  -2.750  -0.2344   0.02038   0.01077  -0.0267   1.0000   0.4922
  -2.500  -0.2174   0.01919   0.01047  -0.0234   1.0000   0.6319
  -2.250  -0.1409   0.01829   0.01029  -0.0271   1.0000   1.0000
  -2.000  -0.1345   0.01810   0.00968  -0.0254   1.0000   1.0000
  -1.750  -0.1191   0.01815   0.00939  -0.0244   1.0000   1.0000
  -1.500  -0.1017   0.01830   0.00924  -0.0236   1.0000   1.0000
  -1.250  -0.0834   0.01850   0.00920  -0.0229   1.0000   1.0000
  -1.000  -0.0647   0.01877   0.00924  -0.0223   1.0000   1.0000
  -0.750  -0.0459   0.01909   0.00937  -0.0218   1.0000   1.0000
  -0.500  -0.0269   0.01947   0.00959  -0.0214   1.0000   1.0000
  -0.250  -0.0081   0.01991   0.00988  -0.0210   1.0000   1.0000
   0.000   0.0106   0.02041   0.01026  -0.0208   1.0000   1.0000
   0.250   0.0291   0.02098   0.01072  -0.0206   1.0000   1.0000
   0.500   0.0474   0.02162   0.01127  -0.0206   1.0000   1.0000
   0.750   0.0654   0.02232   0.01189  -0.0206   1.0000   1.0000
   1.000   0.0831   0.02310   0.01261  -0.0207   1.0000   1.0000
   1.250   0.1321   0.02423   0.01368  -0.0266   0.9872   1.0000
   1.500   0.1864   0.02532   0.01475  -0.0332   0.9693   1.0000
   1.750   0.2382   0.02630   0.01573  -0.0390   0.9511   1.0000
   2.000   0.2908   0.02718   0.01664  -0.0447   0.9333   1.0000
   2.250   0.3334   0.02791   0.01743  -0.0483   0.9138   1.0000
   2.500   0.3748   0.02858   0.01816  -0.0515   0.8943   1.0000
   2.750   0.4197   0.02913   0.01881  -0.0550   0.8755   1.0000
   3.000   0.4688   0.02950   0.01931  -0.0587   0.8576   1.0000
   3.250   0.5023   0.02999   0.01992  -0.0599   0.8371   1.0000
   3.500   0.5444   0.03022   0.02032  -0.0619   0.8175   1.0000
   3.750   0.5894   0.03012   0.02040  -0.0637   0.7988   1.0000
   4.000   0.6266   0.03010   0.02055  -0.0640   0.7788   1.0000
   4.250   0.6587   0.03012   0.02073  -0.0635   0.7568   1.0000
   4.500   0.7013   0.02942   0.02024  -0.0634   0.7365   1.0000
   4.750   0.7289   0.02935   0.02032  -0.0616   0.7116   1.0000
   5.000   0.7651   0.02851   0.01964  -0.0599   0.6867   1.0000
   5.250   0.7983   0.02762   0.01887  -0.0575   0.6581   1.0000
   5.500   0.8240   0.02715   0.01849  -0.0545   0.6249   1.0000
   5.750   0.8494   0.02663   0.01800  -0.0514   0.5878   1.0000
   6.000   0.8727   0.02611   0.01745  -0.0479   0.5444   1.0000
   6.250   0.8928   0.02559   0.01673  -0.0440   0.4916   1.0000
   6.500   0.9060   0.02563   0.01652  -0.0398   0.4266   1.0000
   6.750   0.9147   0.02638   0.01679  -0.0354   0.3469   1.0000
   7.000   0.9239   0.02807   0.01781  -0.0318   0.2731   1.0000
   7.250   0.9416   0.03024   0.01958  -0.0298   0.2261   1.0000
   7.500   0.9635   0.03234   0.02148  -0.0286   0.1977   1.0000
   7.750   0.9877   0.03445   0.02348  -0.0277   0.1790   1.0000
   8.000   1.0133   0.03694   0.02613  -0.0270   0.1677   1.0000
   8.250   1.0379   0.03960   0.02887  -0.0264   0.1591   1.0000
   8.500   1.0574   0.04201   0.03161  -0.0252   0.1505   1.0000
   8.750   1.0762   0.04511   0.03495  -0.0241   0.1450   1.0000
   9.000   1.0875   0.04859   0.03902  -0.0222   0.1421   1.0000
   9.250   1.0964   0.05208   0.04295  -0.0203   0.1387   1.0000
   9.500   1.1176   0.05544   0.04616  -0.0200   0.1327   1.0000
   9.750   1.1145   0.05948   0.05081  -0.0174   0.1315   1.0000
  10.000   1.1104   0.06405   0.05583  -0.0153   0.1314   1.0000
  10.250   1.1007   0.06884   0.06100  -0.0133   0.1317   1.0000
  10.500   1.0872   0.07378   0.06624  -0.0116   0.1320   1.0000
  10.750   1.0720   0.07888   0.07155  -0.0103   0.1325   1.0000
  11.000   0.9600   0.08957   0.08260  -0.0137   0.1430   1.0000
  11.250   0.8907   0.10813   0.10107  -0.0274   0.1593   1.0000
  11.500   0.8893   0.11454   0.10748  -0.0291   0.1610   1.0000
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