Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 2.5411 (naca2411-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 2.5411 (naca2411-il)
Reynolds number: 1,000,000
Max Cl/Cd: 113.73 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca2411-il-1000000.txt
Download as CSV file: xf-naca2411-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.500  -0.7712   0.09876   0.09662  -0.0387   1.0000   0.0146
 -15.250  -0.8289   0.08407   0.08178  -0.0474   1.0000   0.0144
 -15.000  -0.8872   0.07008   0.06763  -0.0562   1.0000   0.0143
 -14.750  -0.9347   0.05805   0.05543  -0.0644   1.0000   0.0142
 -14.500  -0.9636   0.04839   0.04558  -0.0723   1.0000   0.0142
 -14.250  -0.9775   0.04183   0.03885  -0.0783   1.0000   0.0142
 -14.000  -0.9934   0.03672   0.03356  -0.0821   1.0000   0.0142
 -13.750  -1.0053   0.03363   0.03033  -0.0824   1.0000   0.0143
 -13.500  -1.0123   0.03185   0.02844  -0.0804   1.0000   0.0143
 -13.250  -1.0213   0.03063   0.02711  -0.0764   1.0000   0.0144
 -13.000  -1.0286   0.02954   0.02593  -0.0720   1.0000   0.0145
 -12.750  -1.0328   0.02810   0.02435  -0.0682   1.0000   0.0146
 -12.500  -1.0465   0.02584   0.02190  -0.0632   1.0000   0.0148
 -12.250  -1.0472   0.02441   0.02035  -0.0594   1.0000   0.0150
 -12.000  -1.0420   0.02335   0.01920  -0.0563   1.0000   0.0152
 -11.750  -1.0331   0.02252   0.01830  -0.0536   1.0000   0.0154
 -11.500  -1.0066   0.02162   0.01733  -0.0543   0.9988   0.0158
 -11.250  -0.9771   0.02094   0.01658  -0.0555   0.9974   0.0161
 -11.000  -0.9477   0.02016   0.01572  -0.0566   0.9958   0.0165
 -10.750  -0.9175   0.01939   0.01485  -0.0578   0.9946   0.0170
 -10.500  -0.8891   0.01861   0.01397  -0.0585   0.9929   0.0173
 -10.250  -0.8608   0.01794   0.01320  -0.0591   0.9907   0.0176
 -10.000  -0.8307   0.01737   0.01255  -0.0600   0.9887   0.0178
  -9.750  -0.8040   0.01598   0.01102  -0.0608   0.9867   0.0184
  -9.500  -0.7730   0.01522   0.01021  -0.0619   0.9853   0.0190
  -9.250  -0.7402   0.01469   0.00965  -0.0633   0.9842   0.0195
  -9.000  -0.7067   0.01421   0.00912  -0.0648   0.9834   0.0202
  -8.750  -0.6822   0.01378   0.00864  -0.0643   0.9791   0.0207
  -8.500  -0.6513   0.01332   0.00812  -0.0651   0.9768   0.0213
  -8.250  -0.6184   0.01295   0.00770  -0.0662   0.9752   0.0217
  -8.000  -0.5871   0.01211   0.00679  -0.0673   0.9736   0.0228
  -7.750  -0.5530   0.01164   0.00631  -0.0688   0.9725   0.0239
  -7.500  -0.5172   0.01126   0.00590  -0.0706   0.9716   0.0250
  -7.250  -0.4878   0.01095   0.00556  -0.0709   0.9677   0.0260
  -7.000  -0.4582   0.01046   0.00503  -0.0713   0.9635   0.0276
  -6.750  -0.4261   0.01009   0.00466  -0.0723   0.9605   0.0297
  -6.500  -0.3929   0.00981   0.00435  -0.0734   0.9580   0.0315
  -6.250  -0.3663   0.00943   0.00398  -0.0731   0.9527   0.0349
  -6.000  -0.3380   0.00921   0.00374  -0.0731   0.9472   0.0377
  -5.750  -0.3072   0.00887   0.00341  -0.0737   0.9430   0.0424
  -5.500  -0.2809   0.00870   0.00323  -0.0733   0.9361   0.0460
  -5.250  -0.2529   0.00843   0.00298  -0.0733   0.9296   0.0521
  -5.000  -0.2255   0.00823   0.00277  -0.0731   0.9227   0.0574
  -4.750  -0.1984   0.00804   0.00258  -0.0728   0.9148   0.0636
  -4.500  -0.1714   0.00784   0.00240  -0.0725   0.9069   0.0715
  -4.250  -0.1444   0.00768   0.00223  -0.0722   0.8982   0.0803
  -4.000  -0.1180   0.00751   0.00209  -0.0718   0.8890   0.0911
  -3.750  -0.0911   0.00735   0.00194  -0.0715   0.8798   0.1047
  -3.500  -0.0653   0.00718   0.00182  -0.0710   0.8690   0.1215
  -3.250  -0.0391   0.00703   0.00170  -0.0705   0.8585   0.1401
  -3.000  -0.0129   0.00690   0.00159  -0.0700   0.8474   0.1597
  -2.750   0.0130   0.00677   0.00150  -0.0695   0.8352   0.1809
  -2.500   0.0388   0.00665   0.00142  -0.0690   0.8227   0.2053
  -2.250   0.0645   0.00653   0.00135  -0.0684   0.8099   0.2315
  -2.000   0.0902   0.00643   0.00128  -0.0679   0.7967   0.2594
  -1.750   0.1157   0.00634   0.00123  -0.0673   0.7828   0.2896
  -1.500   0.1409   0.00624   0.00118  -0.0666   0.7680   0.3229
  -1.250   0.1660   0.00615   0.00114  -0.0660   0.7531   0.3596
  -1.000   0.1906   0.00601   0.00111  -0.0652   0.7378   0.4087
  -0.750   0.2142   0.00583   0.00109  -0.0643   0.7218   0.4812
  -0.500   0.2375   0.00564   0.00109  -0.0633   0.7057   0.5581
  -0.250   0.2607   0.00550   0.00110  -0.0622   0.6893   0.6271
   0.000   0.2835   0.00538   0.00112  -0.0610   0.6729   0.6931
   0.250   0.3057   0.00526   0.00115  -0.0596   0.6564   0.7592
   0.500   0.3278   0.00516   0.00119  -0.0581   0.6405   0.8217
   0.750   0.3514   0.00510   0.00126  -0.0569   0.6242   0.8827
   1.000   0.3830   0.00514   0.00135  -0.0574   0.6073   0.9289
   1.250   0.4216   0.00527   0.00143  -0.0597   0.5899   0.9538
   1.500   0.4613   0.00542   0.00151  -0.0622   0.5720   0.9667
   1.750   0.4996   0.00558   0.00159  -0.0644   0.5551   0.9748
   2.000   0.5329   0.00574   0.00168  -0.0655   0.5391   0.9824
   2.250   0.5711   0.00588   0.00175  -0.0677   0.5227   0.9863
   2.500   0.6080   0.00604   0.00183  -0.0697   0.5057   0.9906
   2.750   0.6436   0.00620   0.00192  -0.0714   0.4885   0.9944
   3.000   0.6829   0.00634   0.00199  -0.0739   0.4717   0.9976
   3.250   0.7209   0.00649   0.00206  -0.0762   0.4521   1.0000
   3.500   0.7424   0.00663   0.00213  -0.0749   0.4338   1.0000
   3.750   0.7641   0.00677   0.00222  -0.0736   0.4184   1.0000
   4.000   0.7859   0.00691   0.00231  -0.0723   0.4025   1.0000
   4.250   0.8071   0.00711   0.00242  -0.0709   0.3805   1.0000
   4.500   0.8280   0.00732   0.00255  -0.0695   0.3590   1.0000
   4.750   0.8490   0.00755   0.00269  -0.0681   0.3356   1.0000
   5.000   0.8689   0.00785   0.00286  -0.0665   0.3068   1.0000
   5.250   0.8888   0.00817   0.00305  -0.0649   0.2789   1.0000
   5.500   0.9078   0.00855   0.00329  -0.0632   0.2461   1.0000
   5.750   0.9255   0.00903   0.00356  -0.0613   0.2079   1.0000
   6.000   0.9440   0.00946   0.00384  -0.0595   0.1766   1.0000
   6.250   0.9626   0.00990   0.00414  -0.0578   0.1483   1.0000
   6.500   0.9811   0.01036   0.00445  -0.0560   0.1224   1.0000
   6.750   1.0002   0.01078   0.00477  -0.0544   0.1015   1.0000
   7.000   1.0191   0.01121   0.00509  -0.0527   0.0845   1.0000
   7.250   1.0386   0.01159   0.00542  -0.0512   0.0715   1.0000
   7.500   1.0580   0.01199   0.00575  -0.0496   0.0611   1.0000
   7.750   1.0778   0.01235   0.00608  -0.0482   0.0538   1.0000
   8.000   1.0978   0.01270   0.00641  -0.0467   0.0476   1.0000
   8.250   1.1169   0.01310   0.00678  -0.0452   0.0420   1.0000
   8.500   1.1363   0.01347   0.00714  -0.0437   0.0379   1.0000
   8.750   1.1552   0.01386   0.00753  -0.0421   0.0343   1.0000
   9.000   1.1737   0.01426   0.00792  -0.0405   0.0312   1.0000
   9.250   1.1912   0.01471   0.00838  -0.0387   0.0283   1.0000
   9.500   1.2091   0.01511   0.00879  -0.0369   0.0263   1.0000
   9.750   1.2212   0.01570   0.00939  -0.0342   0.0240   1.0000
  10.000   1.2374   0.01605   0.00977  -0.0322   0.0230   1.0000
  10.250   1.2523   0.01648   0.01024  -0.0300   0.0218   1.0000
  10.500   1.2662   0.01698   0.01075  -0.0277   0.0208   1.0000
  10.750   1.2755   0.01775   0.01157  -0.0248   0.0195   1.0000
  11.000   1.2903   0.01825   0.01212  -0.0228   0.0192   1.0000
  11.250   1.3047   0.01879   0.01270  -0.0208   0.0185   1.0000
  11.500   1.3179   0.01940   0.01337  -0.0188   0.0180   1.0000
  11.750   1.3307   0.02006   0.01407  -0.0168   0.0174   1.0000
  12.000   1.3419   0.02083   0.01488  -0.0147   0.0170   1.0000
  12.250   1.3505   0.02178   0.01588  -0.0125   0.0165   1.0000
  12.500   1.3531   0.02315   0.01733  -0.0097   0.0160   1.0000
  12.750   1.3625   0.02416   0.01840  -0.0078   0.0157   1.0000
  13.000   1.3729   0.02512   0.01945  -0.0062   0.0155   1.0000
  13.250   1.3835   0.02614   0.02053  -0.0048   0.0151   1.0000
  13.500   1.3911   0.02740   0.02187  -0.0032   0.0149   1.0000
  13.750   1.3984   0.02875   0.02330  -0.0019   0.0147   1.0000
  14.000   1.4056   0.03018   0.02479  -0.0006   0.0143   1.0000
  14.250   1.4113   0.03180   0.02648   0.0005   0.0141   1.0000
  14.500   1.4165   0.03354   0.02829   0.0014   0.0139   1.0000
  14.750   1.4193   0.03558   0.03041   0.0023   0.0137   1.0000
  15.000   1.4217   0.03774   0.03265   0.0029   0.0135   1.0000
  15.250   1.4191   0.04052   0.03552   0.0034   0.0133   1.0000
  15.500   1.4163   0.04343   0.03851   0.0036   0.0131   1.0000
  15.750   1.4107   0.04677   0.04196   0.0036   0.0129   1.0000
  16.000   1.3951   0.05136   0.04668   0.0034   0.0127   1.0000
  16.250   1.3974   0.05407   0.04949   0.0030   0.0126   1.0000
  16.500   1.3979   0.05708   0.05259   0.0024   0.0125   1.0000
  16.750   1.3927   0.06084   0.05646   0.0016   0.0124   1.0000
  17.000   1.3917   0.06419   0.05991   0.0007   0.0123   1.0000
  17.250   1.3855   0.06826   0.06408  -0.0004   0.0122   1.0000
  17.500   1.3811   0.07222   0.06815  -0.0016   0.0120   1.0000
  17.750   1.3721   0.07683   0.07287  -0.0031   0.0120   1.0000
  18.000   1.3650   0.08128   0.07742  -0.0046   0.0119   1.0000
  18.250   1.3551   0.08619   0.08244  -0.0064   0.0119   1.0000
  18.500   1.3464   0.09110   0.08745  -0.0083   0.0117   1.0000
  18.750   1.3361   0.09630   0.09275  -0.0104   0.0116   1.0000
  19.000   1.3255   0.10164   0.09819  -0.0126   0.0116   1.0000
<< Back to NACA 2.5411 (naca2411-il)

Polar data table (+)

Polar graphs


<< Back to NACA 2.5411 (naca2411-il)