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K3311 (original) (k3311-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: K3311 (original) (k3311-il)
Reynolds number: 500,000
Max Cl/Cd: 107.35 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-k3311-il-500000.txt
Download as CSV file: xf-k3311-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3797   0.08734   0.08510  -0.0396   1.0000   0.0230
  -9.000  -0.3823   0.08378   0.08158  -0.0406   1.0000   0.0232
  -8.750  -0.3869   0.08027   0.07810  -0.0415   1.0000   0.0240
  -8.250  -0.3518   0.05090   0.04889  -0.0603   0.9943   0.0265
  -8.000  -0.4208   0.06805   0.06606  -0.0472   0.9968   0.0248
  -7.750  -0.4016   0.05172   0.04917  -0.0712   0.9851   0.0265
  -7.500  -0.4007   0.04100   0.03799  -0.0779   0.9758   0.0273
  -7.000  -0.3443   0.03677   0.03372  -0.0832   0.9691   0.0293
  -6.750  -0.3199   0.03377   0.03047  -0.0850   0.9617   0.0313
  -6.500  -0.2959   0.02879   0.02473  -0.0872   0.9551   0.0356
  -6.250  -0.2702   0.02695   0.02292  -0.0880   0.9463   0.0369
  -6.000  -0.2415   0.02543   0.02127  -0.0892   0.9386   0.0389
  -5.750  -0.2074   0.02742   0.02293  -0.0892   0.9288   0.0440
  -5.500  -0.1916   0.02222   0.01760  -0.0895   0.9167   0.0479
  -5.250  -0.1655   0.02145   0.01667  -0.0893   0.9053   0.0522
  -5.000  -0.1427   0.01996   0.01495  -0.0890   0.8931   0.0588
  -4.500  -0.0881   0.01518   0.00915  -0.0858   0.8692   0.0346
  -4.250  -0.0631   0.01382   0.00767  -0.0851   0.8565   0.0339
  -4.000  -0.0379   0.01297   0.00671  -0.0845   0.8439   0.0339
  -3.750  -0.0127   0.01228   0.00592  -0.0838   0.8314   0.0339
  -3.500   0.0127   0.01180   0.00534  -0.0832   0.8188   0.0341
  -3.250   0.0374   0.01121   0.00467  -0.0824   0.8063   0.0347
  -3.000   0.0616   0.01063   0.00400  -0.0816   0.7938   0.0351
  -2.750   0.0862   0.01017   0.00346  -0.0809   0.7819   0.0357
  -2.500   0.1115   0.00985   0.00305  -0.0803   0.7712   0.0365
  -2.250   0.1373   0.00961   0.00272  -0.0798   0.7612   0.0377
  -2.000   0.1635   0.00943   0.00248  -0.0794   0.7508   0.0388
  -1.750   0.1899   0.00928   0.00227  -0.0790   0.7407   0.0404
  -1.500   0.2163   0.00918   0.00209  -0.0786   0.7308   0.0431
  -1.250   0.2426   0.00907   0.00193  -0.0781   0.7193   0.0491
  -1.000   0.2658   0.00842   0.00177  -0.0775   0.7075   0.2061
  -0.750   0.2864   0.00756   0.00173  -0.0765   0.6969   0.4707
  -0.500   0.3100   0.00732   0.00176  -0.0756   0.6877   0.5791
  -0.250   0.3341   0.00716   0.00178  -0.0747   0.6782   0.6482
   0.000   0.3577   0.00701   0.00183  -0.0737   0.6693   0.7177
   0.250   0.3802   0.00686   0.00188  -0.0723   0.6607   0.7970
   0.500   0.4057   0.00667   0.00193  -0.0714   0.6519   0.8832
   0.750   0.4852   0.00666   0.00195  -0.0826   0.6414   0.9853
   1.000   0.5241   0.00674   0.00196  -0.0851   0.6317   1.0000
   1.250   0.5486   0.00680   0.00198  -0.0844   0.6219   1.0000
   1.500   0.5731   0.00687   0.00199  -0.0837   0.6117   1.0000
   2.000   0.6220   0.00703   0.00203  -0.0822   0.5883   1.0000
   2.250   0.6467   0.00712   0.00208  -0.0815   0.5780   1.0000
   2.500   0.6713   0.00724   0.00214  -0.0808   0.5685   1.0000
   2.750   0.6960   0.00736   0.00221  -0.0802   0.5587   1.0000
   3.000   0.7210   0.00748   0.00231  -0.0796   0.5496   1.0000
   3.250   0.7456   0.00764   0.00241  -0.0789   0.5411   1.0000
   3.500   0.7706   0.00776   0.00252  -0.0783   0.5309   1.0000
   3.750   0.7954   0.00790   0.00263  -0.0777   0.5202   1.0000
   4.000   0.8200   0.00807   0.00277  -0.0771   0.5109   1.0000
   4.250   0.8449   0.00820   0.00289  -0.0765   0.5000   1.0000
   4.500   0.8696   0.00835   0.00303  -0.0759   0.4884   1.0000
   4.750   0.8941   0.00851   0.00319  -0.0752   0.4768   1.0000
   5.000   0.9185   0.00869   0.00334  -0.0745   0.4648   1.0000
   5.250   0.9428   0.00886   0.00351  -0.0739   0.4530   1.0000
   5.500   0.9671   0.00904   0.00368  -0.0732   0.4386   1.0000
   5.750   0.9908   0.00923   0.00386  -0.0724   0.4195   1.0000
   6.000   1.0135   0.00948   0.00405  -0.0715   0.3954   1.0000
   6.250   1.0350   0.00982   0.00428  -0.0704   0.3665   1.0000
   6.500   1.0550   0.01027   0.00458  -0.0691   0.3337   1.0000
   6.750   1.0750   0.01075   0.00494  -0.0678   0.3029   1.0000
   7.000   1.0950   0.01122   0.00530  -0.0666   0.2726   1.0000
   7.250   1.1130   0.01184   0.00573  -0.0650   0.2343   1.0000
   7.500   1.1291   0.01259   0.00626  -0.0632   0.1924   1.0000
   7.750   1.1410   0.01362   0.00695  -0.0608   0.1336   1.0000
   8.000   1.1497   0.01483   0.00783  -0.0579   0.0815   1.0000
   8.250   1.1529   0.01636   0.00898  -0.0541   0.0309   1.0000
   8.500   1.1650   0.01723   0.00986  -0.0516   0.0247   1.0000
   8.750   1.1790   0.01783   0.01053  -0.0493   0.0227   1.0000
   9.000   1.1903   0.01851   0.01126  -0.0466   0.0207   1.0000
   9.250   1.1971   0.01945   0.01225  -0.0434   0.0192   1.0000
   9.500   1.2043   0.02040   0.01330  -0.0404   0.0182   1.0000
   9.750   1.2143   0.02122   0.01420  -0.0379   0.0175   1.0000
  10.000   1.2227   0.02217   0.01523  -0.0354   0.0170   1.0000
  10.250   1.2296   0.02326   0.01640  -0.0329   0.0164   1.0000
  10.500   1.2358   0.02446   0.01766  -0.0306   0.0157   1.0000
  10.750   1.2400   0.02586   0.01913  -0.0283   0.0152   1.0000
  11.000   1.2414   0.02757   0.02091  -0.0260   0.0147   1.0000
  11.250   1.2361   0.02994   0.02338  -0.0235   0.0143   1.0000
  11.500   1.2394   0.03179   0.02533  -0.0218   0.0139   1.0000
  11.750   1.2475   0.03327   0.02691  -0.0206   0.0135   1.0000
  12.000   1.2529   0.03506   0.02879  -0.0194   0.0133   1.0000
  12.250   1.2587   0.03686   0.03068  -0.0184   0.0129   1.0000
  12.500   1.2633   0.03884   0.03274  -0.0173   0.0126   1.0000
  12.750   1.2677   0.04090   0.03489  -0.0164   0.0123   1.0000
  13.000   1.2720   0.04303   0.03711  -0.0155   0.0121   1.0000
  13.250   1.2764   0.04517   0.03935  -0.0148   0.0119   1.0000
  13.500   1.2803   0.04743   0.04170  -0.0141   0.0116   1.0000
  13.750   1.2834   0.04976   0.04408  -0.0137   0.0113   1.0000
  14.000   1.2870   0.05220   0.04663  -0.0129   0.0113   1.0000
  14.250   1.2902   0.05474   0.04926  -0.0123   0.0111   1.0000
  14.500   1.2932   0.05752   0.05213  -0.0115   0.0108   1.0000
  14.750   1.2944   0.06095   0.05573  -0.0105   0.0107   1.0000
  15.000   1.2936   0.06412   0.05905  -0.0105   0.0107   1.0000
  15.250   1.2818   0.06887   0.06403  -0.0110   0.0105   1.0000
  15.500   1.2736   0.07291   0.06825  -0.0122   0.0104   1.0000
  15.750   1.2653   0.07733   0.07285  -0.0136   0.0103   1.0000
  16.000   1.2562   0.08208   0.07777  -0.0151   0.0103   1.0000
  16.250   1.2453   0.08728   0.08315  -0.0173   0.0102   1.0000
  16.500   1.2336   0.09289   0.08895  -0.0197   0.0101   1.0000
  16.750   1.2208   0.09888   0.09511  -0.0223   0.0102   1.0000
  17.000   1.2037   0.10597   0.10240  -0.0259   0.0101   1.0000
  17.250   1.1900   0.11265   0.10924  -0.0294   0.0101   1.0000
  17.500   1.1740   0.12009   0.11684  -0.0336   0.0101   1.0000
  17.750   1.1564   0.12814   0.12505  -0.0382   0.0102   1.0000
  18.000   1.1391   0.13646   0.13352  -0.0433   0.0103   1.0000
  18.250   1.1194   0.14579   0.14299  -0.0490   0.0103   1.0000
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