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NACA 2408 (naca2408-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 2408 (naca2408-il)
Reynolds number: 200,000
Max Cl/Cd: 66.56 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca2408-il-200000.txt
Download as CSV file: xf-naca2408-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2408                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5291   0.10873   0.10513  -0.0095   1.0000   0.0456
  -9.500  -0.5315   0.10450   0.10095  -0.0147   1.0000   0.0462
  -9.250  -0.5311   0.10015   0.09664  -0.0185   1.0000   0.0464
  -9.000  -0.5313   0.09548   0.09201  -0.0224   1.0000   0.0465
  -8.750  -0.5356   0.08915   0.08572  -0.0219   1.0000   0.0476
  -8.500  -0.5264   0.08667   0.08325  -0.0197   1.0000   0.0489
  -8.250  -0.5215   0.08365   0.08025  -0.0201   1.0000   0.0503
  -8.000  -0.5206   0.07999   0.07662  -0.0222   1.0000   0.0516
  -7.750  -0.5179   0.07533   0.07198  -0.0269   1.0000   0.0533
  -7.500  -0.5145   0.06959   0.06622  -0.0332   1.0000   0.0557
  -7.250  -0.5147   0.06179   0.05796  -0.0441   1.0000   0.0592
  -7.000  -0.5168   0.05445   0.05059  -0.0450   1.0000   0.0605
  -6.750  -0.5019   0.05384   0.05020  -0.0421   1.0000   0.0633
  -6.500  -0.4914   0.05089   0.04716  -0.0420   1.0000   0.0671
  -6.250  -0.4916   0.03815   0.03357  -0.0440   1.0000   0.0500
  -6.000  -0.4840   0.02727   0.02132  -0.0423   1.0000   0.0380
  -5.750  -0.4648   0.02541   0.01928  -0.0413   1.0000   0.0399
  -5.500  -0.4444   0.02373   0.01727  -0.0401   1.0000   0.0433
  -5.250  -0.4225   0.02174   0.01479  -0.0389   1.0000   0.0455
  -5.000  -0.4003   0.01933   0.01204  -0.0381   1.0000   0.0492
  -4.750  -0.3776   0.01848   0.01112  -0.0373   1.0000   0.0541
  -4.500  -0.3537   0.01764   0.01003  -0.0364   1.0000   0.0585
  -4.250  -0.3296   0.01628   0.00861  -0.0359   1.0000   0.0641
  -4.000  -0.3054   0.01565   0.00787  -0.0353   1.0000   0.0690
  -3.750  -0.2809   0.01509   0.00720  -0.0347   1.0000   0.0737
  -3.500  -0.2558   0.01423   0.00638  -0.0344   1.0000   0.0783
  -3.250  -0.2307   0.01383   0.00595  -0.0340   1.0000   0.0848
  -3.000  -0.2047   0.01321   0.00536  -0.0339   1.0000   0.0930
  -2.750  -0.1785   0.01270   0.00492  -0.0338   1.0000   0.1083
  -2.500  -0.1512   0.01199   0.00454  -0.0342   1.0000   0.1681
  -2.250  -0.1245   0.01146   0.00443  -0.0347   1.0000   0.2675
  -2.000  -0.0870   0.01090   0.00437  -0.0373   0.9967   0.3951
  -1.750  -0.0495   0.00996   0.00443  -0.0396   0.9929   0.6396
  -1.500  -0.0179   0.00929   0.00459  -0.0387   0.9883   0.9370
  -1.250   0.0318   0.00928   0.00444  -0.0435   0.9816   1.0000
  -1.000   0.0775   0.00932   0.00434  -0.0474   0.9759   1.0000
  -0.750   0.1190   0.00931   0.00423  -0.0503   0.9674   1.0000
  -0.500   0.1625   0.00927   0.00411  -0.0536   0.9602   1.0000
  -0.250   0.2067   0.00920   0.00397  -0.0569   0.9530   1.0000
   0.000   0.2450   0.00911   0.00385  -0.0590   0.9430   1.0000
   0.250   0.2838   0.00900   0.00370  -0.0610   0.9336   1.0000
   0.500   0.3191   0.00887   0.00355  -0.0621   0.9224   1.0000
   0.750   0.3495   0.00877   0.00343  -0.0622   0.9082   1.0000
   1.000   0.3776   0.00869   0.00333  -0.0617   0.8923   1.0000
   1.250   0.4037   0.00864   0.00326  -0.0609   0.8739   1.0000
   1.500   0.4299   0.00861   0.00319  -0.0600   0.8549   1.0000
   1.750   0.4554   0.00860   0.00313  -0.0589   0.8327   1.0000
   2.000   0.4799   0.00860   0.00305  -0.0576   0.8048   1.0000
   2.250   0.5042   0.00866   0.00300  -0.0562   0.7728   1.0000
   2.500   0.5289   0.00877   0.00302  -0.0551   0.7419   1.0000
   2.750   0.5536   0.00893   0.00306  -0.0541   0.7101   1.0000
   3.000   0.5779   0.00913   0.00312  -0.0530   0.6745   1.0000
   3.250   0.6024   0.00935   0.00324  -0.0520   0.6390   1.0000
   3.500   0.6270   0.00960   0.00338  -0.0511   0.6055   1.0000
   3.750   0.6517   0.00987   0.00356  -0.0503   0.5716   1.0000
   4.000   0.6762   0.01016   0.00378  -0.0496   0.5370   1.0000
   4.250   0.6998   0.01052   0.00399  -0.0486   0.4909   1.0000
   4.500   0.7225   0.01098   0.00423  -0.0476   0.4312   1.0000
   4.750   0.7441   0.01159   0.00455  -0.0465   0.3530   1.0000
   5.000   0.7603   0.01302   0.00518  -0.0449   0.1950   1.0000
   5.250   0.7766   0.01479   0.00623  -0.0434   0.0894   1.0000
   5.500   0.7989   0.01566   0.00708  -0.0425   0.0764   1.0000
   5.750   0.8212   0.01649   0.00796  -0.0415   0.0696   1.0000
   6.000   0.8438   0.01727   0.00876  -0.0406   0.0639   1.0000
   6.250   0.8639   0.01851   0.01002  -0.0393   0.0600   1.0000
   6.500   0.8873   0.01924   0.01086  -0.0385   0.0559   1.0000
   6.750   0.9095   0.02024   0.01188  -0.0376   0.0520   1.0000
   7.000   0.9302   0.02200   0.01365  -0.0365   0.0479   1.0000
   7.250   0.9537   0.02321   0.01502  -0.0356   0.0446   1.0000
   7.500   0.9761   0.02456   0.01647  -0.0348   0.0407   1.0000
   7.750   0.9971   0.02791   0.01997  -0.0339   0.0372   1.0000
   8.000   1.0191   0.02969   0.02209  -0.0326   0.0356   1.0000
   8.250   1.0391   0.03179   0.02454  -0.0313   0.0334   1.0000
   8.500   1.0575   0.03378   0.02678  -0.0300   0.0310   1.0000
   8.750   1.0737   0.03661   0.02990  -0.0285   0.0300   1.0000
   9.000   1.0857   0.04016   0.03387  -0.0266   0.0297   1.0000
   9.250   1.0832   0.04638   0.04093  -0.0229   0.0316   1.0000
   9.500   1.0778   0.05213   0.04720  -0.0199   0.0333   1.0000
   9.750   1.0700   0.05717   0.05260  -0.0175   0.0344   1.0000
  10.000   1.0588   0.06200   0.05770  -0.0153   0.0353   1.0000
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