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K3311 (smoothed) (k3311sm-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: K3311 (smoothed) (k3311sm-il)
Reynolds number: 500,000
Max Cl/Cd: 101.08 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-k3311sm-il-500000-n5.txt
Download as CSV file: xf-k3311sm-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: K3311 (smoothed)                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3951   0.08571   0.08344  -0.0405   1.0000   0.0092
  -9.250  -0.4014   0.08139   0.07916  -0.0419   1.0000   0.0090
  -9.000  -0.4123   0.07664   0.07446  -0.0433   1.0000   0.0090
  -8.750  -0.4250   0.07089   0.06876  -0.0466   0.9989   0.0089
  -8.500  -0.5144   0.02587   0.02205  -0.0823   0.9603   0.0089
  -8.250  -0.4936   0.02195   0.01755  -0.0834   0.9526   0.0093
  -8.000  -0.4675   0.01963   0.01483  -0.0844   0.9449   0.0097
  -7.750  -0.4399   0.01811   0.01300  -0.0851   0.9364   0.0100
  -7.500  -0.4107   0.01684   0.01147  -0.0860   0.9279   0.0103
  -7.250  -0.3845   0.01577   0.01025  -0.0861   0.9166   0.0107
  -7.000  -0.3570   0.01518   0.00954  -0.0863   0.9055   0.0111
  -6.750  -0.3298   0.01473   0.00899  -0.0864   0.8936   0.0116
  -6.500  -0.3036   0.01424   0.00838  -0.0862   0.8813   0.0123
  -6.250  -0.2781   0.01370   0.00767  -0.0858   0.8687   0.0130
  -6.000  -0.2531   0.01319   0.00701  -0.0852   0.8556   0.0136
  -5.750  -0.2293   0.01254   0.00624  -0.0845   0.8427   0.0143
  -5.500  -0.2044   0.01215   0.00577  -0.0840   0.8296   0.0151
  -5.250  -0.1791   0.01183   0.00536  -0.0835   0.8171   0.0160
  -5.000  -0.1539   0.01152   0.00494  -0.0830   0.8045   0.0170
  -4.750  -0.1285   0.01124   0.00455  -0.0824   0.7921   0.0180
  -4.500  -0.1036   0.01091   0.00414  -0.0819   0.7801   0.0196
  -4.250  -0.0779   0.01071   0.00387  -0.0814   0.7679   0.0212
  -4.000  -0.0521   0.01049   0.00357  -0.0810   0.7562   0.0228
  -3.750  -0.0261   0.01033   0.00331  -0.0805   0.7449   0.0242
  -3.500  -0.0008   0.01006   0.00300  -0.0800   0.7339   0.0270
  -3.250   0.0253   0.00990   0.00276  -0.0796   0.7230   0.0296
  -3.000   0.0515   0.00976   0.00255  -0.0792   0.7124   0.0322
  -2.750   0.0776   0.00959   0.00235  -0.0788   0.7022   0.0378
  -2.500   0.1038   0.00948   0.00217  -0.0785   0.6923   0.0438
  -2.250   0.1302   0.00935   0.00202  -0.0781   0.6824   0.0529
  -2.000   0.1563   0.00920   0.00189  -0.0778   0.6729   0.0709
  -1.750   0.1815   0.00892   0.00175  -0.0773   0.6636   0.1265
  -1.500   0.2058   0.00847   0.00163  -0.0769   0.6543   0.2394
  -1.250   0.2304   0.00813   0.00156  -0.0764   0.6455   0.3388
  -1.000   0.2552   0.00788   0.00153  -0.0759   0.6365   0.4226
  -0.750   0.2802   0.00768   0.00154  -0.0754   0.6279   0.5025
  -0.250   0.3296   0.00740   0.00158  -0.0740   0.6104   0.6325
   0.000   0.3550   0.00734   0.00158  -0.0734   0.6020   0.6695
   0.250   0.3808   0.00731   0.00159  -0.0729   0.5929   0.6985
   0.500   0.4062   0.00727   0.00161  -0.0723   0.5842   0.7318
   1.000   0.4557   0.00715   0.00167  -0.0708   0.5665   0.8161
   1.250   0.4824   0.00706   0.00171  -0.0703   0.5580   0.8758
   1.500   0.5389   0.00708   0.00178  -0.0766   0.5470   0.9475
   1.750   0.5875   0.00716   0.00182  -0.0812   0.5364   0.9903
   2.000   0.6184   0.00728   0.00188  -0.0820   0.5271   1.0000
   2.250   0.6430   0.00740   0.00195  -0.0813   0.5178   1.0000
   2.500   0.6679   0.00750   0.00201  -0.0807   0.5081   1.0000
   2.750   0.6926   0.00762   0.00209  -0.0801   0.4987   1.0000
   3.250   0.7421   0.00788   0.00228  -0.0788   0.4784   1.0000
   3.500   0.7668   0.00802   0.00238  -0.0782   0.4685   1.0000
   3.750   0.7913   0.00817   0.00249  -0.0776   0.4576   1.0000
   4.000   0.8160   0.00832   0.00261  -0.0770   0.4464   1.0000
   4.250   0.8407   0.00848   0.00276  -0.0763   0.4347   1.0000
   4.500   0.8651   0.00865   0.00290  -0.0757   0.4224   1.0000
   4.750   0.8892   0.00885   0.00306  -0.0750   0.4086   1.0000
   5.000   0.9132   0.00905   0.00323  -0.0743   0.3943   1.0000
   5.250   0.9370   0.00927   0.00342  -0.0736   0.3797   1.0000
   5.500   0.9606   0.00951   0.00362  -0.0728   0.3644   1.0000
   5.750   0.9838   0.00977   0.00384  -0.0720   0.3477   1.0000
   6.000   1.0063   0.01008   0.00409  -0.0711   0.3287   1.0000
   6.250   1.0274   0.01048   0.00439  -0.0700   0.3012   1.0000
   6.500   1.0463   0.01104   0.00475  -0.0686   0.2621   1.0000
   6.750   1.0655   0.01157   0.00513  -0.0672   0.2305   1.0000
   7.000   1.0846   0.01212   0.00554  -0.0658   0.2011   1.0000
   7.250   1.1029   0.01271   0.00599  -0.0644   0.1708   1.0000
   7.500   1.1203   0.01334   0.00647  -0.0628   0.1410   1.0000
   7.750   1.1373   0.01398   0.00698  -0.0611   0.1149   1.0000
   8.000   1.1537   0.01464   0.00753  -0.0594   0.0917   1.0000
   8.250   1.1685   0.01536   0.00813  -0.0574   0.0687   1.0000
   8.500   1.1830   0.01607   0.00876  -0.0554   0.0500   1.0000
   8.750   1.1967   0.01678   0.00939  -0.0532   0.0371   1.0000
   9.000   1.2097   0.01739   0.00999  -0.0509   0.0295   1.0000
   9.250   1.2233   0.01794   0.01057  -0.0486   0.0255   1.0000
   9.500   1.2350   0.01860   0.01124  -0.0462   0.0216   1.0000
   9.750   1.2485   0.01919   0.01188  -0.0441   0.0195   1.0000
  10.000   1.2599   0.01992   0.01264  -0.0418   0.0173   1.0000
  10.250   1.2712   0.02067   0.01345  -0.0396   0.0156   1.0000
  10.500   1.2833   0.02141   0.01425  -0.0376   0.0147   1.0000
  10.750   1.2940   0.02225   0.01516  -0.0356   0.0136   1.0000
  11.000   1.3030   0.02324   0.01620  -0.0336   0.0126   1.0000
  11.250   1.3097   0.02443   0.01746  -0.0314   0.0118   1.0000
  11.500   1.3192   0.02548   0.01860  -0.0297   0.0113   1.0000
  11.750   1.3281   0.02663   0.01984  -0.0281   0.0108   1.0000
  12.000   1.3365   0.02786   0.02114  -0.0267   0.0102   1.0000
  12.250   1.3437   0.02924   0.02260  -0.0253   0.0098   1.0000
  12.500   1.3496   0.03081   0.02425  -0.0239   0.0093   1.0000
  12.750   1.3530   0.03265   0.02618  -0.0227   0.0090   1.0000
  13.000   1.3540   0.03483   0.02844  -0.0215   0.0087   1.0000
  13.250   1.3564   0.03695   0.03067  -0.0207   0.0084   1.0000
  13.500   1.3603   0.03902   0.03284  -0.0200   0.0082   1.0000
  13.750   1.3625   0.04132   0.03525  -0.0194   0.0080   1.0000
  14.000   1.3623   0.04395   0.03801  -0.0190   0.0078   1.0000
  14.250   1.3627   0.04661   0.04077  -0.0188   0.0075   1.0000
  14.500   1.3646   0.04916   0.04342  -0.0187   0.0072   1.0000
  14.750   1.3641   0.05206   0.04643  -0.0187   0.0070   1.0000
  15.000   1.3599   0.05552   0.05000  -0.0190   0.0070   1.0000
  15.250   1.3601   0.05853   0.05310  -0.0193   0.0067   1.0000
  15.500   1.3592   0.06176   0.05641  -0.0199   0.0064   1.0000
  15.750   1.3536   0.06571   0.06046  -0.0207   0.0063   1.0000
  16.000   1.3450   0.07019   0.06506  -0.0217   0.0062   1.0000
  16.250   1.3368   0.07474   0.06972  -0.0229   0.0061   1.0000
  16.500   1.3301   0.07919   0.07428  -0.0242   0.0060   1.0000
  16.750   1.3233   0.08377   0.07899  -0.0256   0.0059   1.0000
  17.000   1.3176   0.08831   0.08365  -0.0272   0.0058   1.0000
  17.250   1.3107   0.09311   0.08858  -0.0289   0.0057   1.0000
  17.500   1.3027   0.09817   0.09376  -0.0308   0.0057   1.0000
  17.750   1.2956   0.10320   0.09891  -0.0328   0.0056   1.0000
  18.000   1.2879   0.10844   0.10428  -0.0350   0.0055   1.0000
  18.250   1.2800   0.11379   0.10975  -0.0374   0.0055   1.0000
  18.500   1.2723   0.11923   0.11532  -0.0399   0.0053   1.0000
  18.750   1.2633   0.12497   0.12118  -0.0426   0.0053   1.0000
  19.000   1.2555   0.13063   0.12696  -0.0455   0.0052   1.0000
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