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NACA 2.5411 (naca2411-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 2.5411 (naca2411-il)
Reynolds number: 50,000
Max Cl/Cd: 35.91 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca2411-il-50000-n5.txt
Download as CSV file: xf-naca2411-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2.5411                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4528   0.09762   0.08989  -0.0393   1.0000   0.0677
  -9.750  -0.4613   0.09263   0.08498  -0.0414   1.0000   0.0672
  -9.250  -0.5225   0.07543   0.06800  -0.0527   1.0000   0.0644
  -9.000  -0.5441   0.07095   0.06355  -0.0528   1.0000   0.0642
  -8.750  -0.5632   0.06639   0.05895  -0.0527   1.0000   0.0641
  -8.500  -0.5816   0.06184   0.05427  -0.0521   1.0000   0.0642
  -8.250  -0.5981   0.05724   0.04940  -0.0508   1.0000   0.0646
  -8.000  -0.5921   0.05539   0.04761  -0.0491   1.0000   0.0660
  -7.750  -0.5876   0.05338   0.04555  -0.0473   1.0000   0.0678
  -7.500  -0.5879   0.05030   0.04222  -0.0456   1.0000   0.0692
  -7.250  -0.5869   0.04697   0.03858  -0.0439   1.0000   0.0706
  -7.000  -0.5831   0.04363   0.03482  -0.0421   1.0000   0.0720
  -6.750  -0.5763   0.04044   0.03110  -0.0403   1.0000   0.0742
  -6.500  -0.5655   0.03796   0.02822  -0.0386   1.0000   0.0771
  -6.250  -0.5509   0.03662   0.02684  -0.0371   1.0000   0.0804
  -6.000  -0.5359   0.03479   0.02472  -0.0355   1.0000   0.0840
  -5.750  -0.5197   0.03283   0.02221  -0.0340   1.0000   0.0888
  -5.500  -0.5028   0.03176   0.02121  -0.0327   1.0000   0.0934
  -5.250  -0.4845   0.03044   0.01962  -0.0313   1.0000   0.0993
  -5.000  -0.4662   0.02933   0.01841  -0.0300   1.0000   0.1057
  -4.750  -0.4472   0.02836   0.01725  -0.0287   1.0000   0.1136
  -4.500  -0.4282   0.02752   0.01638  -0.0275   1.0000   0.1220
  -4.250  -0.4083   0.02672   0.01543  -0.0263   1.0000   0.1324
  -4.000  -0.3888   0.02609   0.01473  -0.0251   1.0000   0.1447
  -3.750  -0.3693   0.02550   0.01414  -0.0240   1.0000   0.1580
  -3.500  -0.3352   0.02494   0.01359  -0.0257   0.9944   0.1792
  -3.000  -0.2607   0.02398   0.01272  -0.0303   0.9783   0.2417
  -2.750  -0.2225   0.02357   0.01242  -0.0328   0.9705   0.2863
  -2.500  -0.1890   0.02308   0.01215  -0.0344   0.9609   0.3381
  -2.250  -0.1555   0.02257   0.01194  -0.0358   0.9517   0.4050
  -2.000  -0.1220   0.02201   0.01188  -0.0369   0.9432   0.5023
  -1.750  -0.0956   0.02145   0.01189  -0.0361   0.9329   0.6322
  -1.500  -0.0424   0.02107   0.01210  -0.0391   0.9282   0.8402
  -1.250   0.0510   0.02115   0.01194  -0.0516   0.9272   1.0000
  -1.000   0.0825   0.02119   0.01174  -0.0528   0.9145   1.0000
  -0.750   0.1151   0.02125   0.01158  -0.0541   0.9023   1.0000
  -0.500   0.1508   0.02130   0.01145  -0.0559   0.8914   1.0000
  -0.250   0.1895   0.02131   0.01130  -0.0580   0.8812   1.0000
   0.000   0.2200   0.02137   0.01122  -0.0586   0.8684   1.0000
   0.250   0.2519   0.02141   0.01115  -0.0594   0.8561   1.0000
   0.500   0.2857   0.02140   0.01105  -0.0604   0.8448   1.0000
   0.750   0.3209   0.02137   0.01093  -0.0616   0.8338   1.0000
   1.000   0.3486   0.02144   0.01094  -0.0614   0.8202   1.0000
   1.500   0.4064   0.02156   0.01097  -0.0613   0.7940   1.0000
   1.750   0.4373   0.02158   0.01096  -0.0616   0.7816   1.0000
   2.000   0.4707   0.02154   0.01090  -0.0621   0.7701   1.0000
   2.250   0.4969   0.02166   0.01101  -0.0615   0.7559   1.0000
   2.500   0.5233   0.02179   0.01113  -0.0609   0.7417   1.0000
   2.750   0.5499   0.02192   0.01127  -0.0603   0.7275   1.0000
   3.000   0.5766   0.02206   0.01142  -0.0597   0.7135   1.0000
   3.250   0.6034   0.02220   0.01158  -0.0592   0.6993   1.0000
   3.500   0.6302   0.02236   0.01176  -0.0585   0.6851   1.0000
   3.750   0.6568   0.02252   0.01195  -0.0579   0.6707   1.0000
   4.000   0.6831   0.02270   0.01215  -0.0571   0.6559   1.0000
   4.250   0.7087   0.02290   0.01241  -0.0563   0.6407   1.0000
   4.500   0.7336   0.02312   0.01267  -0.0553   0.6250   1.0000
   4.750   0.7576   0.02337   0.01297  -0.0542   0.6086   1.0000
   5.000   0.7809   0.02364   0.01332  -0.0530   0.5914   1.0000
   5.250   0.8038   0.02391   0.01365  -0.0516   0.5736   1.0000
   5.500   0.8265   0.02418   0.01397  -0.0502   0.5549   1.0000
   5.750   0.8494   0.02441   0.01423  -0.0488   0.5353   1.0000
   6.000   0.8697   0.02471   0.01460  -0.0470   0.5140   1.0000
   6.250   0.8884   0.02503   0.01497  -0.0450   0.4908   1.0000
   6.500   0.9066   0.02535   0.01530  -0.0429   0.4663   1.0000
   6.750   0.9230   0.02570   0.01568  -0.0406   0.4399   1.0000
   7.000   0.9368   0.02615   0.01617  -0.0380   0.4111   1.0000
   7.250   0.9496   0.02665   0.01665  -0.0352   0.3802   1.0000
   7.500   0.9608   0.02724   0.01718  -0.0324   0.3473   1.0000
   7.750   0.9701   0.02798   0.01783  -0.0294   0.3124   1.0000
   8.000   0.9776   0.02891   0.01866  -0.0264   0.2767   1.0000
   8.250   0.9835   0.03005   0.01962  -0.0234   0.2430   1.0000
   8.500   0.9870   0.03135   0.02075  -0.0202   0.2130   1.0000
   8.750   0.9904   0.03282   0.02207  -0.0172   0.1876   1.0000
   9.000   0.9932   0.03443   0.02353  -0.0145   0.1671   1.0000
   9.250   0.9973   0.03612   0.02511  -0.0120   0.1499   1.0000
   9.500   1.0025   0.03785   0.02681  -0.0098   0.1359   1.0000
   9.750   1.0082   0.03962   0.02855  -0.0079   0.1240   1.0000
  10.000   1.0168   0.04137   0.03037  -0.0062   0.1135   1.0000
  10.250   1.0254   0.04318   0.03223  -0.0046   0.1049   1.0000
  10.500   1.0350   0.04499   0.03402  -0.0032   0.0979   1.0000
  10.750   1.0466   0.04687   0.03608  -0.0019   0.0909   1.0000
  11.000   1.0572   0.04872   0.03795  -0.0007   0.0854   1.0000
  11.250   1.0699   0.05082   0.04025   0.0004   0.0804   1.0000
  11.500   1.0787   0.05298   0.04258   0.0015   0.0760   1.0000
  11.750   1.0926   0.05492   0.04444   0.0023   0.0723   1.0000
  12.000   1.0973   0.05778   0.04767   0.0034   0.0696   1.0000
  12.250   1.0983   0.06075   0.05094   0.0043   0.0671   1.0000
  12.500   1.0983   0.06370   0.05410   0.0050   0.0648   1.0000
  12.750   1.1001   0.06650   0.05700   0.0055   0.0628   1.0000
  13.000   1.1061   0.06937   0.05990   0.0059   0.0612   1.0000
  13.250   1.0925   0.07392   0.06480   0.0057   0.0606   1.0000
  13.500   1.0753   0.07910   0.07029   0.0047   0.0601   1.0000
  13.750   1.0554   0.08494   0.07641   0.0029   0.0599   1.0000
  14.000   1.0313   0.09180   0.08352  -0.0001   0.0598   1.0000
  14.250   1.0039   0.09983   0.09178  -0.0043   0.0600   1.0000
  14.500   0.9741   0.10920   0.10131  -0.0097   0.0603   1.0000
  14.750   0.9410   0.12054   0.11276  -0.0166   0.0607   1.0000
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