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K3311 (smoothed) (k3311sm-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: K3311 (smoothed) (k3311sm-il)
Reynolds number: 100,000
Max Cl/Cd: 57.04 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-k3311sm-il-100000-n5.txt
Download as CSV file: xf-k3311sm-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3986   0.07796   0.07329  -0.0478   1.0000   0.0314
  -8.000  -0.4086   0.07531   0.07074  -0.0468   1.0000   0.0311
  -7.750  -0.4199   0.07186   0.06737  -0.0470   1.0000   0.0308
  -7.500  -0.4317   0.06863   0.06417  -0.0466   1.0000   0.0305
  -7.250  -0.4437   0.06557   0.06113  -0.0456   1.0000   0.0301
  -7.000  -0.4286   0.05872   0.05407  -0.0529   0.9912   0.0295
  -6.750  -0.4094   0.05199   0.04701  -0.0594   0.9815   0.0289
  -6.500  -0.3886   0.04596   0.04053  -0.0641   0.9721   0.0286
  -6.250  -0.3671   0.04090   0.03496  -0.0669   0.9624   0.0285
  -6.000  -0.3396   0.03643   0.02990  -0.0696   0.9554   0.0289
  -5.750  -0.3136   0.03305   0.02590  -0.0707   0.9464   0.0303
  -5.500  -0.2831   0.03012   0.02231  -0.0722   0.9397   0.0322
  -5.250  -0.2539   0.02793   0.01986  -0.0732   0.9320   0.0335
  -5.000  -0.2201   0.02597   0.01756  -0.0747   0.9264   0.0349
  -4.750  -0.1908   0.02445   0.01578  -0.0751   0.9176   0.0369
  -4.500  -0.1567   0.02322   0.01419  -0.0762   0.9111   0.0407
  -4.250  -0.1274   0.02167   0.01254  -0.0764   0.9025   0.0429
  -4.000  -0.0964   0.02054   0.01135  -0.0771   0.8947   0.0459
  -3.750  -0.0654   0.01973   0.01041  -0.0776   0.8863   0.0514
  -3.500  -0.0377   0.01878   0.00943  -0.0775   0.8767   0.0554
  -3.250  -0.0061   0.01800   0.00857  -0.0781   0.8693   0.0621
  -3.000   0.0199   0.01738   0.00790  -0.0777   0.8583   0.0717
  -2.750   0.0479   0.01676   0.00724  -0.0777   0.8486   0.0858
  -2.500   0.0768   0.01594   0.00661  -0.0779   0.8401   0.1305
  -2.250   0.0980   0.01469   0.00631  -0.0772   0.8290   0.3559
  -2.000   0.1223   0.01412   0.00625  -0.0763   0.8190   0.5202
  -1.750   0.1488   0.01377   0.00614  -0.0754   0.8104   0.6252
  -1.500   0.1699   0.01344   0.00617  -0.0731   0.7995   0.7360
  -1.250   0.1980   0.01318   0.00606  -0.0720   0.7900   0.8231
  -1.000   0.2398   0.01302   0.00582  -0.0742   0.7816   0.8784
  -0.750   0.2916   0.01293   0.00560  -0.0789   0.7714   0.9319
  -0.500   0.3426   0.01287   0.00535  -0.0836   0.7618   0.9824
  -0.250   0.3776   0.01290   0.00518  -0.0852   0.7521   1.0000
   0.000   0.4003   0.01299   0.00512  -0.0844   0.7407   1.0000
   0.250   0.4243   0.01309   0.00507  -0.0836   0.7302   1.0000
   0.500   0.4494   0.01319   0.00501  -0.0830   0.7207   1.0000
   0.750   0.4737   0.01331   0.00502  -0.0823   0.7101   1.0000
   1.000   0.4981   0.01345   0.00506  -0.0817   0.6999   1.0000
   1.250   0.5235   0.01357   0.00507  -0.0811   0.6905   1.0000
   1.500   0.5484   0.01372   0.00514  -0.0805   0.6804   1.0000
   1.750   0.5729   0.01388   0.00524  -0.0798   0.6701   1.0000
   2.000   0.5984   0.01404   0.00531  -0.0793   0.6608   1.0000
   2.250   0.6234   0.01420   0.00541  -0.0787   0.6507   1.0000
   2.500   0.6480   0.01439   0.00558  -0.0780   0.6404   1.0000
   2.750   0.6732   0.01456   0.00570  -0.0775   0.6309   1.0000
   3.000   0.6983   0.01475   0.00585  -0.0769   0.6209   1.0000
   3.250   0.7227   0.01495   0.00605  -0.0762   0.6103   1.0000
   3.500   0.7476   0.01515   0.00625  -0.0756   0.6003   1.0000
   3.750   0.7729   0.01534   0.00642  -0.0750   0.5905   1.0000
   4.000   0.7968   0.01557   0.00667  -0.0743   0.5793   1.0000
   4.250   0.8211   0.01579   0.00691  -0.0736   0.5685   1.0000
   4.500   0.8457   0.01601   0.00716  -0.0729   0.5578   1.0000
   4.750   0.8701   0.01623   0.00739  -0.0722   0.5468   1.0000
   5.000   0.8936   0.01648   0.00770  -0.0714   0.5346   1.0000
   5.250   0.9171   0.01673   0.00803  -0.0705   0.5226   1.0000
   5.500   0.9405   0.01699   0.00834  -0.0697   0.5103   1.0000
   5.750   0.9638   0.01726   0.00865  -0.0688   0.4977   1.0000
   6.000   0.9866   0.01754   0.00898  -0.0679   0.4844   1.0000
   6.250   1.0090   0.01783   0.00935  -0.0669   0.4704   1.0000
   6.500   1.0309   0.01814   0.00973  -0.0658   0.4554   1.0000
   6.750   1.0522   0.01846   0.01013  -0.0646   0.4396   1.0000
   7.000   1.0729   0.01881   0.01055  -0.0633   0.4229   1.0000
   7.250   1.0930   0.01919   0.01101  -0.0620   0.4054   1.0000
   7.500   1.1120   0.01960   0.01145  -0.0604   0.3866   1.0000
   7.750   1.1293   0.02006   0.01196  -0.0587   0.3636   1.0000
   8.000   1.1442   0.02060   0.01247  -0.0566   0.3359   1.0000
   8.250   1.1567   0.02128   0.01305  -0.0542   0.3039   1.0000
   8.500   1.1671   0.02209   0.01376  -0.0517   0.2712   1.0000
   8.750   1.1767   0.02299   0.01457  -0.0491   0.2385   1.0000
   9.000   1.1839   0.02402   0.01549  -0.0463   0.2059   1.0000
   9.250   1.1880   0.02515   0.01650  -0.0431   0.1759   1.0000
   9.500   1.1898   0.02647   0.01767  -0.0398   0.1453   1.0000
   9.750   1.1905   0.02797   0.01903  -0.0366   0.1161   1.0000
  10.000   1.1896   0.02970   0.02062  -0.0336   0.0912   1.0000
  10.250   1.1888   0.03153   0.02237  -0.0309   0.0733   1.0000
  10.500   1.1878   0.03348   0.02430  -0.0285   0.0618   1.0000
  10.750   1.1866   0.03557   0.02643  -0.0264   0.0540   1.0000
  11.000   1.1845   0.03783   0.02872  -0.0245   0.0483   1.0000
  11.250   1.1839   0.04009   0.03108  -0.0230   0.0442   1.0000
  11.500   1.1831   0.04249   0.03361  -0.0217   0.0409   1.0000
  11.750   1.1803   0.04518   0.03638  -0.0207   0.0387   1.0000
  12.000   1.1762   0.04812   0.03938  -0.0198   0.0369   1.0000
  12.250   1.1773   0.05065   0.04210  -0.0191   0.0350   1.0000
  12.500   1.1776   0.05335   0.04493  -0.0186   0.0330   1.0000
  12.750   1.1770   0.05621   0.04789  -0.0183   0.0311   1.0000
  13.000   1.1754   0.05923   0.05099  -0.0181   0.0297   1.0000
  13.250   1.1745   0.06223   0.05402  -0.0177   0.0286   1.0000
  13.500   1.1784   0.06484   0.05685  -0.0173   0.0277   1.0000
  13.750   1.1821   0.06755   0.05974  -0.0168   0.0268   1.0000
  14.000   1.1850   0.07043   0.06279  -0.0166   0.0258   1.0000
  14.250   1.1857   0.07364   0.06617  -0.0168   0.0248   1.0000
  14.500   1.1850   0.07705   0.06971  -0.0173   0.0239   1.0000
  14.750   1.1834   0.08063   0.07340  -0.0180   0.0230   1.0000
  15.000   1.1827   0.08417   0.07705  -0.0186   0.0224   1.0000
  15.250   1.1803   0.08807   0.08102  -0.0193   0.0216   1.0000
  15.500   1.1748   0.09269   0.08589  -0.0207   0.0213   1.0000
  15.750   1.1672   0.09778   0.09123  -0.0225   0.0211   1.0000
  16.000   1.1572   0.10344   0.09714  -0.0249   0.0209   1.0000
  16.250   1.1458   0.10954   0.10347  -0.0278   0.0207   1.0000
  16.500   1.1322   0.11631   0.11046  -0.0313   0.0206   1.0000
  16.750   1.1177   0.12356   0.11793  -0.0353   0.0206   1.0000
  17.000   1.1010   0.13164   0.12622  -0.0401   0.0207   1.0000
  17.250   1.0826   0.14066   0.13542  -0.0458   0.0207   1.0000
  17.500   1.0624   0.15072   0.14564  -0.0522   0.0209   1.0000
  17.750   1.0419   0.16164   0.15668  -0.0590   0.0212   1.0000
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