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NACA 2.5411 (naca2411-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 2.5411 (naca2411-il)
Reynolds number: 100,000
Max Cl/Cd: 52.92 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca2411-il-100000.txt
Download as CSV file: xf-naca2411-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4120   0.09791   0.09263  -0.0317   1.0000   0.1404
  -9.000  -0.4572   0.09559   0.09052  -0.0371   1.0000   0.1453
  -8.750  -0.4522   0.09116   0.08613  -0.0361   1.0000   0.1470
  -8.500  -0.4232   0.08852   0.08344  -0.0323   1.0000   0.1514
  -8.250  -0.4354   0.08603   0.08104  -0.0325   1.0000   0.1578
  -8.000  -0.4738   0.08349   0.07868  -0.0332   1.0000   0.1596
  -7.750  -0.5209   0.07922   0.07447  -0.0366   1.0000   0.1614
  -7.500  -0.5938   0.05461   0.04901  -0.0433   1.0000   0.0894
  -7.250  -0.5886   0.05118   0.04549  -0.0415   1.0000   0.0873
  -7.000  -0.5889   0.04724   0.04131  -0.0397   1.0000   0.0867
  -6.750  -0.5871   0.04329   0.03702  -0.0377   1.0000   0.0863
  -6.500  -0.5816   0.03963   0.03298  -0.0358   1.0000   0.0859
  -6.250  -0.5729   0.03620   0.02911  -0.0339   1.0000   0.0858
  -6.000  -0.5612   0.03321   0.02560  -0.0321   1.0000   0.0865
  -5.750  -0.5468   0.03107   0.02283  -0.0301   1.0000   0.0885
  -5.500  -0.5303   0.02905   0.02079  -0.0290   1.0000   0.0921
  -5.250  -0.5119   0.02783   0.01943  -0.0277   1.0000   0.0963
  -5.000  -0.4926   0.02637   0.01754  -0.0262   1.0000   0.1006
  -4.750  -0.4735   0.02510   0.01620  -0.0251   1.0000   0.1065
  -4.500  -0.4539   0.02428   0.01519  -0.0238   1.0000   0.1138
  -4.250  -0.4345   0.02332   0.01421  -0.0227   1.0000   0.1216
  -4.000  -0.4148   0.02266   0.01333  -0.0214   1.0000   0.1314
  -3.750  -0.3958   0.02200   0.01277  -0.0203   1.0000   0.1423
  -3.500  -0.3768   0.02139   0.01220  -0.0191   1.0000   0.1545
  -3.250  -0.3480   0.02096   0.01177  -0.0198   0.9970   0.1732
  -3.000  -0.3063   0.02054   0.01149  -0.0230   0.9891   0.2008
  -2.750  -0.2646   0.02022   0.01128  -0.0261   0.9813   0.2397
  -2.500  -0.2245   0.01981   0.01116  -0.0288   0.9726   0.2889
  -2.250  -0.1886   0.01935   0.01103  -0.0308   0.9631   0.3520
  -2.000  -0.1496   0.01880   0.01105  -0.0332   0.9553   0.4453
  -1.750  -0.1176   0.01807   0.01115  -0.0338   0.9455   0.6067
  -1.500  -0.0171   0.01750   0.01149  -0.0457   0.9474   0.9733
  -1.250   0.0496   0.01772   0.01140  -0.0537   0.9427   1.0000
  -1.000   0.0875   0.01775   0.01124  -0.0561   0.9303   1.0000
  -0.750   0.1274   0.01778   0.01110  -0.0587   0.9190   1.0000
  -0.500   0.1808   0.01771   0.01089  -0.0636   0.9120   1.0000
  -0.250   0.2174   0.01766   0.01073  -0.0653   0.8994   1.0000
   0.000   0.2590   0.01756   0.01054  -0.0678   0.8887   1.0000
   0.250   0.3138   0.01724   0.01015  -0.0727   0.8817   1.0000
   0.500   0.3493   0.01708   0.00994  -0.0738   0.8691   1.0000
   0.750   0.3877   0.01685   0.00967  -0.0754   0.8575   1.0000
   1.000   0.4354   0.01643   0.00921  -0.0785   0.8492   1.0000
   1.250   0.4658   0.01628   0.00903  -0.0785   0.8352   1.0000
   1.500   0.4960   0.01615   0.00886  -0.0784   0.8211   1.0000
   1.750   0.5259   0.01603   0.00872  -0.0781   0.8068   1.0000
   2.000   0.5548   0.01594   0.00860  -0.0778   0.7924   1.0000
   2.250   0.5830   0.01588   0.00852  -0.0772   0.7777   1.0000
   2.500   0.6102   0.01587   0.00848  -0.0765   0.7628   1.0000
   2.750   0.6366   0.01589   0.00847  -0.0756   0.7476   1.0000
   3.000   0.6623   0.01595   0.00852  -0.0747   0.7321   1.0000
   3.250   0.6874   0.01605   0.00858  -0.0736   0.7164   1.0000
   3.500   0.7120   0.01617   0.00868  -0.0724   0.7004   1.0000
   3.750   0.7362   0.01631   0.00881  -0.0712   0.6840   1.0000
   4.000   0.7600   0.01647   0.00894  -0.0699   0.6673   1.0000
   4.250   0.7836   0.01664   0.00909  -0.0686   0.6503   1.0000
   4.500   0.8071   0.01681   0.00923  -0.0673   0.6328   1.0000
   4.750   0.8308   0.01696   0.00936  -0.0659   0.6146   1.0000
   5.000   0.8542   0.01713   0.00948  -0.0645   0.5956   1.0000
   5.250   0.8739   0.01734   0.00972  -0.0625   0.5745   1.0000
   5.500   0.8952   0.01752   0.00988  -0.0608   0.5532   1.0000
   5.750   0.9163   0.01770   0.01001  -0.0590   0.5312   1.0000
   6.000   0.9348   0.01791   0.01023  -0.0568   0.5070   1.0000
   6.250   0.9538   0.01814   0.01042  -0.0547   0.4826   1.0000
   6.500   0.9712   0.01837   0.01065  -0.0524   0.4561   1.0000
   6.750   0.9869   0.01865   0.01093  -0.0499   0.4268   1.0000
   7.000   1.0011   0.01896   0.01120  -0.0471   0.3939   1.0000
   7.250   1.0128   0.01939   0.01154  -0.0440   0.3544   1.0000
   7.500   1.0215   0.02004   0.01202  -0.0406   0.3076   1.0000
   7.750   1.0264   0.02108   0.01271  -0.0367   0.2561   1.0000
   8.000   1.0297   0.02247   0.01371  -0.0329   0.2101   1.0000
   8.250   1.0350   0.02393   0.01489  -0.0294   0.1751   1.0000
   8.500   1.0421   0.02543   0.01612  -0.0264   0.1518   1.0000
   8.750   1.0530   0.02685   0.01745  -0.0239   0.1336   1.0000
   9.000   1.0661   0.02831   0.01883  -0.0218   0.1198   1.0000
   9.250   1.0821   0.02990   0.02029  -0.0203   0.1083   1.0000
   9.500   1.0990   0.03131   0.02171  -0.0188   0.0992   1.0000
   9.750   1.1193   0.03309   0.02357  -0.0179   0.0912   1.0000
  10.250   1.1653   0.03715   0.02777  -0.0170   0.0800   1.0000
  10.500   1.1828   0.03892   0.02967  -0.0158   0.0758   1.0000
  10.750   1.2093   0.04193   0.03264  -0.0164   0.0717   1.0000
  11.000   1.2182   0.04413   0.03526  -0.0139   0.0701   1.0000
  11.250   1.2246   0.04667   0.03817  -0.0114   0.0686   1.0000
  11.500   1.2276   0.04919   0.04102  -0.0087   0.0671   1.0000
  11.750   1.2282   0.05155   0.04361  -0.0058   0.0657   1.0000
  12.000   1.2305   0.05397   0.04621  -0.0034   0.0643   1.0000
  12.250   1.2366   0.05655   0.04887  -0.0018   0.0627   1.0000
  12.500   1.2333   0.05987   0.05238   0.0004   0.0621   1.0000
  12.750   1.2215   0.06325   0.05602   0.0032   0.0619   1.0000
  13.000   1.2037   0.06653   0.05959   0.0058   0.0620   1.0000
  13.250   1.1805   0.07025   0.06360   0.0078   0.0623   1.0000
  13.500   1.1408   0.07512   0.06884   0.0087   0.0631   1.0000
  13.750   1.0685   0.08462   0.07884   0.0054   0.0654   1.0000
  14.000   1.0112   0.09602   0.09051  -0.0010   0.0678   1.0000
  14.250   0.9683   0.10766   0.10226  -0.0080   0.0699   1.0000
  14.500   0.9420   0.11779   0.11243  -0.0135   0.0713   1.0000
  14.750   0.9283   0.12622   0.12087  -0.0172   0.0721   1.0000
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