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K3311 (original) (k3311-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: K3311 (original) (k3311-il)
Reynolds number: 100,000
Max Cl/Cd: 55.91 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-k3311-il-100000.txt
Download as CSV file: xf-k3311-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: K3311  (original)                               
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3679   0.11699   0.11179  -0.0318   1.0000   0.0917
 -10.250  -0.3798   0.11509   0.10999  -0.0354   1.0000   0.0948
 -10.000  -0.3987   0.11356   0.10858  -0.0400   1.0000   0.0956
  -9.750  -0.3698   0.10723   0.10219  -0.0355   1.0000   0.0984
  -9.500  -0.3597   0.10424   0.09921  -0.0345   1.0000   0.1025
  -9.250  -0.3638   0.10159   0.09663  -0.0360   1.0000   0.1076
  -9.000  -0.3840   0.09962   0.09481  -0.0398   1.0000   0.1096
  -8.750  -0.3717   0.09515   0.09035  -0.0377   1.0000   0.1130
  -8.500  -0.3616   0.09252   0.08774  -0.0360   1.0000   0.1186
  -8.250  -0.3763   0.09024   0.08559  -0.0375   1.0000   0.1230
  -8.000  -0.4064   0.08858   0.08412  -0.0386   1.0000   0.1242
  -7.750  -0.4388   0.08584   0.08150  -0.0425   1.0000   0.1248
  -7.500  -0.3938   0.08243   0.07806  -0.0335   1.0000   0.1316
  -7.250  -0.4092   0.08041   0.07616  -0.0322   1.0000   0.1350
  -7.000  -0.4427   0.07797   0.07381  -0.0350   1.0000   0.1386
  -6.750  -0.4646   0.07454   0.07041  -0.0359   1.0000   0.1410
  -6.500  -0.4536   0.07284   0.06882  -0.0298   1.0000   0.1441
  -6.250  -0.4594   0.07088   0.06690  -0.0279   1.0000   0.1490
  -6.000  -0.4784   0.06716   0.06308  -0.0312   1.0000   0.1564
  -5.750  -0.4739   0.06549   0.06152  -0.0271   1.0000   0.1599
  -5.500  -0.4648   0.06177   0.05769  -0.0305   0.9971   0.1728
  -5.250  -0.4336   0.05833   0.05419  -0.0341   0.9899   0.1900
  -5.000  -0.4014   0.05507   0.05083  -0.0386   0.9827   0.2180
  -4.750  -0.3729   0.05219   0.04787  -0.0417   0.9739   0.2470
  -4.500  -0.3440   0.04973   0.04539  -0.0433   0.9662   0.2774
  -4.250  -0.2730   0.03219   0.02478  -0.0584   0.9601   0.0899
  -4.000  -0.2342   0.02967   0.02172  -0.0605   0.9537   0.0872
  -3.750  -0.1974   0.02771   0.01921  -0.0619   0.9458   0.0849
  -3.500  -0.1557   0.02620   0.01725  -0.0640   0.9397   0.0829
  -3.250  -0.1202   0.02486   0.01573  -0.0653   0.9313   0.0830
  -3.000  -0.0754   0.02346   0.01428  -0.0682   0.9265   0.0846
  -2.750  -0.0449   0.02267   0.01349  -0.0688   0.9166   0.0893
  -2.500   0.0016   0.02173   0.01251  -0.0720   0.9122   0.0946
  -2.250   0.0289   0.02095   0.01181  -0.0718   0.9016   0.0997
  -2.000   0.0759   0.02000   0.01087  -0.0752   0.8973   0.1153
  -1.750   0.0975   0.01820   0.01041  -0.0746   0.8868   0.3765
  -1.500   0.1267   0.01688   0.01053  -0.0725   0.8824   0.7716
  -1.250   0.2481   0.01623   0.01002  -0.0883   0.8847   0.9928
  -1.000   0.2777   0.01616   0.00971  -0.0895   0.8731   1.0000
  -0.750   0.3091   0.01607   0.00940  -0.0904   0.8633   1.0000
  -0.500   0.3424   0.01596   0.00910  -0.0913   0.8539   1.0000
  -0.250   0.3659   0.01607   0.00905  -0.0906   0.8417   1.0000
   0.000   0.3924   0.01612   0.00896  -0.0902   0.8307   1.0000
   0.250   0.4270   0.01596   0.00865  -0.0910   0.8225   1.0000
   0.500   0.4497   0.01609   0.00866  -0.0898   0.8099   1.0000
   0.750   0.4738   0.01620   0.00868  -0.0889   0.7980   1.0000
   1.000   0.5000   0.01628   0.00867  -0.0883   0.7873   1.0000
   1.250   0.5303   0.01624   0.00852  -0.0882   0.7787   1.0000
   1.500   0.5527   0.01649   0.00871  -0.0871   0.7668   1.0000
   1.750   0.5772   0.01671   0.00887  -0.0864   0.7561   1.0000
   2.000   0.6076   0.01671   0.00878  -0.0863   0.7481   1.0000
   2.250   0.6293   0.01703   0.00910  -0.0852   0.7363   1.0000
   2.500   0.6530   0.01731   0.00936  -0.0843   0.7255   1.0000
   2.750   0.6808   0.01742   0.00942  -0.0839   0.7164   1.0000
   3.000   0.7058   0.01763   0.00961  -0.0832   0.7058   1.0000
   3.250   0.7294   0.01789   0.00990  -0.0823   0.6944   1.0000
   3.500   0.7550   0.01808   0.01007  -0.0816   0.6836   1.0000
   3.750   0.7842   0.01812   0.01006  -0.0813   0.6740   1.0000
   4.000   0.8075   0.01841   0.01038  -0.0803   0.6617   1.0000
   4.250   0.8308   0.01873   0.01076  -0.0793   0.6496   1.0000
   4.500   0.8552   0.01902   0.01109  -0.0785   0.6380   1.0000
   4.750   0.8812   0.01923   0.01132  -0.0778   0.6268   1.0000
   5.000   0.9076   0.01940   0.01153  -0.0772   0.6154   1.0000
   5.250   0.9303   0.01968   0.01189  -0.0761   0.6023   1.0000
   5.500   0.9539   0.01992   0.01221  -0.0751   0.5894   1.0000
   5.750   0.9782   0.02007   0.01242  -0.0741   0.5757   1.0000
   6.000   1.0033   0.02004   0.01243  -0.0731   0.5600   1.0000
   6.250   1.0285   0.01999   0.01237  -0.0719   0.5433   1.0000
   6.500   1.0532   0.02008   0.01246  -0.0709   0.5271   1.0000
   6.750   1.0765   0.02033   0.01278  -0.0698   0.5113   1.0000
   7.000   1.0979   0.02064   0.01322  -0.0685   0.4942   1.0000
   7.250   1.1191   0.02094   0.01364  -0.0671   0.4767   1.0000
   7.500   1.1398   0.02104   0.01377  -0.0654   0.4556   1.0000
   7.750   1.1546   0.02090   0.01364  -0.0626   0.4262   1.0000
   8.000   1.1663   0.02086   0.01358  -0.0594   0.3929   1.0000
   8.250   1.1777   0.02116   0.01391  -0.0565   0.3594   1.0000
   8.500   1.1878   0.02171   0.01440  -0.0536   0.3251   1.0000
   8.750   1.1944   0.02250   0.01511  -0.0502   0.2844   1.0000
   9.000   1.1920   0.02376   0.01609  -0.0458   0.2239   1.0000
   9.250   1.1749   0.02597   0.01769  -0.0397   0.1476   1.0000
   9.500   1.1556   0.02876   0.01995  -0.0341   0.1027   1.0000
   9.750   1.1449   0.03124   0.02221  -0.0300   0.0851   1.0000
  10.000   1.1429   0.03331   0.02429  -0.0270   0.0748   1.0000
  10.250   1.1425   0.03545   0.02646  -0.0245   0.0686   1.0000
  10.500   1.1462   0.03740   0.02843  -0.0224   0.0636   1.0000
  10.750   1.1525   0.03950   0.03047  -0.0206   0.0593   1.0000
  11.000   1.1641   0.04124   0.03231  -0.0191   0.0552   1.0000
  11.250   1.1791   0.04304   0.03408  -0.0179   0.0520   1.0000
  11.500   1.2162   0.04548   0.03650  -0.0176   0.0492   1.0000
  11.750   1.2390   0.04791   0.03923  -0.0168   0.0477   1.0000
  12.000   1.2542   0.05055   0.04214  -0.0158   0.0463   1.0000
  12.250   1.2627   0.05316   0.04499  -0.0145   0.0448   1.0000
  12.500   1.2696   0.05597   0.04801  -0.0132   0.0436   1.0000
  12.750   1.2715   0.05927   0.05160  -0.0118   0.0432   1.0000
  13.000   1.2656   0.06292   0.05559  -0.0104   0.0433   1.0000
  13.250   1.2529   0.06692   0.05992  -0.0091   0.0436   1.0000
  13.500   1.2362   0.07133   0.06466  -0.0085   0.0439   1.0000
  13.750   1.2162   0.07619   0.06983  -0.0085   0.0442   1.0000
  14.000   1.1937   0.08160   0.07553  -0.0094   0.0447   1.0000
  14.250   1.1696   0.08759   0.08179  -0.0112   0.0452   1.0000
  14.500   1.1435   0.09430   0.08873  -0.0139   0.0457   1.0000
  14.750   1.1161   0.10174   0.09639  -0.0177   0.0463   1.0000
  15.000   1.0878   0.11007   0.10489  -0.0225   0.0469   1.0000
  15.250   1.0564   0.11998   0.11497  -0.0287   0.0476   1.0000
  15.500   1.0283   0.13050   0.12559  -0.0354   0.0484   1.0000
  15.750   1.0089   0.14014   0.13526  -0.0410   0.0494   1.0000
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