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NACA 2410 (naca2410-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 2410 (naca2410-il)
Reynolds number: 100,000
Max Cl/Cd: 49.94 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca2410-il-100000-n5.txt
Download as CSV file: xf-naca2410-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5629   0.09185   0.08660  -0.0254   1.0000   0.0367
 -10.000  -0.5764   0.08412   0.07895  -0.0302   1.0000   0.0370
  -9.750  -0.5963   0.07438   0.06927  -0.0370   1.0000   0.0369
  -9.500  -0.6274   0.06309   0.05795  -0.0469   1.0000   0.0361
  -9.250  -0.6545   0.05546   0.05008  -0.0504   1.0000   0.0359
  -9.000  -0.6728   0.04909   0.04331  -0.0511   1.0000   0.0364
  -8.750  -0.6827   0.04362   0.03725  -0.0503   1.0000   0.0373
  -8.500  -0.6828   0.03937   0.03243  -0.0488   1.0000   0.0383
  -8.250  -0.6713   0.03713   0.03002  -0.0476   1.0000   0.0394
  -8.000  -0.6569   0.03559   0.02835  -0.0464   1.0000   0.0411
  -7.750  -0.6424   0.03385   0.02637  -0.0451   1.0000   0.0434
  -7.500  -0.6282   0.03157   0.02363  -0.0436   1.0000   0.0457
  -7.250  -0.6120   0.02947   0.02100  -0.0421   1.0000   0.0476
  -7.000  -0.5941   0.02803   0.01957  -0.0410   1.0000   0.0499
  -6.750  -0.5750   0.02698   0.01838  -0.0399   1.0000   0.0525
  -6.500  -0.5553   0.02566   0.01681  -0.0387   1.0000   0.0549
  -6.250  -0.5347   0.02454   0.01539  -0.0376   1.0000   0.0579
  -6.000  -0.5143   0.02339   0.01418  -0.0366   1.0000   0.0606
  -5.750  -0.4933   0.02250   0.01324  -0.0356   1.0000   0.0632
  -5.500  -0.4718   0.02165   0.01227  -0.0346   1.0000   0.0660
  -5.250  -0.4499   0.02096   0.01141  -0.0336   1.0000   0.0700
  -5.000  -0.4283   0.02016   0.01062  -0.0327   1.0000   0.0736
  -4.750  -0.4063   0.01953   0.00996  -0.0319   1.0000   0.0776
  -4.500  -0.3839   0.01895   0.00928  -0.0310   1.0000   0.0824
  -4.250  -0.3615   0.01836   0.00872  -0.0304   1.0000   0.0885
  -4.000  -0.3246   0.01779   0.00816  -0.0326   0.9951   0.1017
  -3.750  -0.2880   0.01723   0.00764  -0.0347   0.9893   0.1204
  -3.500  -0.2504   0.01673   0.00723  -0.0371   0.9839   0.1467
  -3.250  -0.2148   0.01628   0.00692  -0.0390   0.9771   0.1840
  -3.000  -0.1789   0.01585   0.00668  -0.0410   0.9707   0.2338
  -2.750  -0.1431   0.01538   0.00649  -0.0430   0.9639   0.2979
  -2.500  -0.1091   0.01493   0.00631  -0.0445   0.9564   0.3660
  -2.250  -0.0732   0.01445   0.00614  -0.0463   0.9498   0.4474
  -2.000  -0.0413   0.01397   0.00606  -0.0470   0.9415   0.5472
  -1.750  -0.0087   0.01353   0.00600  -0.0474   0.9343   0.6580
  -1.500   0.0191   0.01321   0.00600  -0.0464   0.9246   0.7625
  -1.250   0.0574   0.01301   0.00599  -0.0473   0.9182   0.8639
  -1.000   0.1046   0.01292   0.00589  -0.0506   0.9099   0.9393
  -0.750   0.1598   0.01281   0.00568  -0.0560   0.9033   0.9868
  -0.500   0.1992   0.01272   0.00549  -0.0583   0.8913   1.0000
  -0.250   0.2290   0.01266   0.00533  -0.0586   0.8774   1.0000
   0.000   0.2582   0.01260   0.00519  -0.0587   0.8630   1.0000
   0.250   0.2867   0.01256   0.00506  -0.0586   0.8480   1.0000
   0.500   0.3148   0.01254   0.00496  -0.0584   0.8324   1.0000
   0.750   0.3424   0.01252   0.00488  -0.0581   0.8162   1.0000
   1.000   0.3697   0.01253   0.00481  -0.0577   0.7994   1.0000
   1.250   0.3969   0.01255   0.00476  -0.0572   0.7824   1.0000
   1.500   0.4233   0.01260   0.00476  -0.0566   0.7644   1.0000
   1.750   0.4493   0.01268   0.00478  -0.0560   0.7456   1.0000
   2.000   0.4754   0.01278   0.00482  -0.0553   0.7267   1.0000
   2.250   0.5014   0.01289   0.00488  -0.0546   0.7078   1.0000
   2.500   0.5273   0.01303   0.00494  -0.0540   0.6889   1.0000
   2.750   0.5526   0.01319   0.00508  -0.0532   0.6686   1.0000
   3.000   0.5779   0.01336   0.00521  -0.0525   0.6485   1.0000
   3.250   0.6033   0.01356   0.00534  -0.0517   0.6286   1.0000
   3.500   0.6282   0.01377   0.00554  -0.0510   0.6074   1.0000
   3.750   0.6531   0.01401   0.00573  -0.0502   0.5860   1.0000
   4.000   0.6776   0.01426   0.00594  -0.0493   0.5631   1.0000
   4.250   0.7017   0.01453   0.00616  -0.0484   0.5381   1.0000
   4.500   0.7254   0.01482   0.00641  -0.0474   0.5112   1.0000
   4.750   0.7490   0.01513   0.00668  -0.0465   0.4843   1.0000
   5.000   0.7721   0.01547   0.00699  -0.0455   0.4539   1.0000
   5.250   0.7935   0.01589   0.00726  -0.0442   0.4118   1.0000
   5.500   0.8139   0.01641   0.00757  -0.0429   0.3591   1.0000
   5.750   0.8340   0.01705   0.00797  -0.0416   0.3065   1.0000
   6.000   0.8542   0.01775   0.00850  -0.0405   0.2573   1.0000
   6.250   0.8733   0.01862   0.00912  -0.0393   0.2071   1.0000
   6.500   0.8916   0.01962   0.00986  -0.0380   0.1598   1.0000
   6.750   0.9098   0.02067   0.01070  -0.0368   0.1232   1.0000
   7.000   0.9281   0.02169   0.01164  -0.0355   0.1013   1.0000
   7.250   0.9462   0.02272   0.01263  -0.0341   0.0883   1.0000
   7.500   0.9639   0.02375   0.01367  -0.0327   0.0798   1.0000
   7.750   0.9816   0.02476   0.01476  -0.0313   0.0738   1.0000
   8.000   0.9992   0.02576   0.01581  -0.0299   0.0685   1.0000
   8.250   1.0151   0.02693   0.01701  -0.0284   0.0645   1.0000
   8.500   1.0329   0.02800   0.01822  -0.0270   0.0615   1.0000
   8.750   1.0501   0.02916   0.01947  -0.0256   0.0587   1.0000
   9.000   1.0666   0.03036   0.02070  -0.0242   0.0559   1.0000
   9.250   1.0829   0.03180   0.02217  -0.0229   0.0533   1.0000
   9.500   1.1010   0.03312   0.02369  -0.0217   0.0509   1.0000
   9.750   1.1181   0.03451   0.02527  -0.0204   0.0485   1.0000
  10.000   1.1333   0.03586   0.02669  -0.0191   0.0461   1.0000
  10.250   1.1484   0.03764   0.02846  -0.0180   0.0439   1.0000
  10.500   1.1629   0.03946   0.03056  -0.0166   0.0422   1.0000
  10.750   1.1744   0.04128   0.03267  -0.0149   0.0402   1.0000
  11.000   1.1824   0.04300   0.03461  -0.0129   0.0383   1.0000
  11.250   1.1894   0.04479   0.03655  -0.0110   0.0368   1.0000
  11.500   1.1961   0.04679   0.03867  -0.0093   0.0357   1.0000
  11.750   1.2005   0.04945   0.04144  -0.0077   0.0345   1.0000
  12.000   1.1949   0.05210   0.04448  -0.0053   0.0336   1.0000
  12.250   1.1871   0.05512   0.04786  -0.0035   0.0326   1.0000
  12.500   1.1776   0.05846   0.05150  -0.0023   0.0318   1.0000
  12.750   1.1663   0.06218   0.05550  -0.0017   0.0311   1.0000
  13.000   1.1527   0.06644   0.06002  -0.0019   0.0307   1.0000
  13.250   1.1362   0.07139   0.06523  -0.0030   0.0304   1.0000
  13.500   1.1164   0.07721   0.07130  -0.0051   0.0303   1.0000
  13.750   1.0921   0.08427   0.07861  -0.0086   0.0303   1.0000
  14.000   1.0615   0.09324   0.08783  -0.0140   0.0306   1.0000
  14.250   1.0213   0.10540   0.10023  -0.0221   0.0312   1.0000
  14.500   0.9700   0.12260   0.11756  -0.0334   0.0326   1.0000
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