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K3311 (smoothed) (k3311sm-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: K3311 (smoothed) (k3311sm-il)
Reynolds number: 200,000
Max Cl/Cd: 77.62 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-k3311sm-il-200000.txt
Download as CSV file: xf-k3311sm-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3561   0.08731   0.08394  -0.0399   1.0000   0.0471
  -8.250  -0.3611   0.08432   0.08100  -0.0403   1.0000   0.0482
  -8.000  -0.3703   0.08145   0.07822  -0.0402   1.0000   0.0491
  -7.750  -0.3886   0.07905   0.07592  -0.0390   1.0000   0.0500
  -7.500  -0.4116   0.07733   0.07432  -0.0364   1.0000   0.0501
  -7.250  -0.4312   0.07511   0.07218  -0.0350   1.0000   0.0500
  -7.000  -0.4276   0.06613   0.06279  -0.0524   0.9923   0.0528
  -6.750  -0.4114   0.05749   0.05395  -0.0596   0.9854   0.0542
  -6.500  -0.3848   0.05404   0.05061  -0.0617   0.9810   0.0559
  -6.250  -0.3572   0.05049   0.04697  -0.0654   0.9744   0.0588
  -6.000  -0.3312   0.04467   0.04035  -0.0720   0.9646   0.0674
  -5.750  -0.3006   0.04160   0.03751  -0.0743   0.9602   0.0713
  -5.500  -0.2705   0.03784   0.03319  -0.0779   0.9534   0.0822
  -5.250  -0.2396   0.03500   0.03036  -0.0799   0.9471   0.0866
  -5.000  -0.2001   0.02514   0.01860  -0.0799   0.9431   0.0423
  -4.750  -0.1691   0.02285   0.01596  -0.0804   0.9353   0.0422
  -4.500  -0.1324   0.02080   0.01383  -0.0827   0.9308   0.0461
  -4.250  -0.0950   0.01911   0.01188  -0.0842   0.9258   0.0479
  -4.000  -0.0627   0.01785   0.01042  -0.0847   0.9176   0.0504
  -3.750  -0.0258   0.01652   0.00894  -0.0861   0.9123   0.0548
  -3.500   0.0020   0.01545   0.00791  -0.0859   0.9021   0.0587
  -3.250   0.0319   0.01476   0.00715  -0.0860   0.8928   0.0647
  -3.000   0.0615   0.01381   0.00621  -0.0862   0.8844   0.0732
  -2.750   0.0864   0.01317   0.00556  -0.0854   0.8728   0.0846
  -2.500   0.1117   0.01246   0.00495  -0.0847   0.8620   0.1202
  -2.250   0.1269   0.01072   0.00472  -0.0828   0.8516   0.4957
  -2.000   0.1499   0.01039   0.00466  -0.0813   0.8410   0.6054
  -1.750   0.1726   0.01019   0.00460  -0.0798   0.8294   0.6726
  -1.500   0.1960   0.01001   0.00453  -0.0783   0.8188   0.7319
  -1.250   0.2201   0.00979   0.00445  -0.0766   0.8094   0.8008
  -1.000   0.2540   0.00958   0.00441  -0.0768   0.7989   0.8932
  -0.750   0.3150   0.00952   0.00425  -0.0832   0.7892   0.9497
  -0.500   0.3701   0.00951   0.00406  -0.0887   0.7797   0.9813
  -0.250   0.4146   0.00951   0.00390  -0.0926   0.7685   1.0000
   0.000   0.4351   0.00958   0.00383  -0.0913   0.7569   1.0000
   0.250   0.4578   0.00967   0.00379  -0.0904   0.7463   1.0000
   0.500   0.4820   0.00977   0.00374  -0.0896   0.7364   1.0000
   0.750   0.5051   0.00988   0.00376  -0.0887   0.7252   1.0000
   1.000   0.5289   0.01000   0.00380  -0.0878   0.7145   1.0000
   1.250   0.5535   0.01013   0.00382  -0.0871   0.7047   1.0000
   1.500   0.5781   0.01026   0.00386  -0.0864   0.6945   1.0000
   1.750   0.6021   0.01040   0.00395  -0.0856   0.6839   1.0000
   2.000   0.6269   0.01055   0.00402  -0.0849   0.6742   1.0000
   2.250   0.6521   0.01069   0.00409  -0.0843   0.6645   1.0000
   2.500   0.6763   0.01084   0.00422  -0.0835   0.6538   1.0000
   2.750   0.7012   0.01100   0.00434  -0.0828   0.6439   1.0000
   3.000   0.7267   0.01116   0.00442  -0.0823   0.6345   1.0000
   3.250   0.7509   0.01131   0.00459  -0.0815   0.6235   1.0000
   3.500   0.7756   0.01148   0.00474  -0.0808   0.6131   1.0000
   3.750   0.8009   0.01165   0.00486  -0.0803   0.6033   1.0000
   4.000   0.8254   0.01181   0.00502  -0.0795   0.5923   1.0000
   4.250   0.8497   0.01198   0.00522  -0.0788   0.5812   1.0000
   4.500   0.8744   0.01216   0.00540  -0.0781   0.5706   1.0000
   4.750   0.8993   0.01235   0.00555  -0.0775   0.5598   1.0000
   5.000   0.9233   0.01252   0.00574  -0.0767   0.5479   1.0000
   5.250   0.9470   0.01271   0.00598  -0.0759   0.5355   1.0000
   5.500   0.9707   0.01290   0.00620  -0.0750   0.5228   1.0000
   5.750   0.9941   0.01309   0.00641  -0.0741   0.5097   1.0000
   6.000   1.0173   0.01330   0.00665  -0.0732   0.4961   1.0000
   6.250   1.0402   0.01352   0.00691  -0.0722   0.4820   1.0000
   6.500   1.0625   0.01374   0.00717  -0.0712   0.4668   1.0000
   6.750   1.0842   0.01398   0.00743  -0.0700   0.4503   1.0000
   7.000   1.1045   0.01423   0.00765  -0.0685   0.4306   1.0000
   7.250   1.1234   0.01448   0.00793  -0.0669   0.4060   1.0000
   7.500   1.1416   0.01482   0.00824  -0.0651   0.3809   1.0000
   7.750   1.1592   0.01523   0.00861  -0.0634   0.3558   1.0000
   8.000   1.1755   0.01572   0.00904  -0.0615   0.3285   1.0000
   8.250   1.1906   0.01628   0.00957  -0.0594   0.2986   1.0000
   8.500   1.2040   0.01695   0.01015  -0.0571   0.2657   1.0000
   8.750   1.2144   0.01778   0.01083  -0.0545   0.2305   1.0000
   9.000   1.2220   0.01878   0.01165  -0.0515   0.1900   1.0000
   9.250   1.2232   0.02003   0.01263  -0.0476   0.1454   1.0000
   9.500   1.2173   0.02171   0.01396  -0.0428   0.0974   1.0000
   9.750   1.2100   0.02362   0.01561  -0.0382   0.0699   1.0000
  10.000   1.2063   0.02541   0.01734  -0.0344   0.0572   1.0000
  10.250   1.2082   0.02696   0.01894  -0.0316   0.0499   1.0000
  10.500   1.2059   0.02888   0.02093  -0.0287   0.0458   1.0000
  10.750   1.2090   0.03056   0.02271  -0.0266   0.0420   1.0000
  11.000   1.2085   0.03261   0.02480  -0.0244   0.0392   1.0000
  11.250   1.2039   0.03525   0.02744  -0.0221   0.0372   1.0000
  11.500   1.2111   0.03694   0.02928  -0.0207   0.0355   1.0000
  11.750   1.2173   0.03876   0.03120  -0.0195   0.0334   1.0000
  12.000   1.2227   0.04071   0.03320  -0.0183   0.0316   1.0000
  12.250   1.2285   0.04277   0.03529  -0.0171   0.0302   1.0000
  12.500   1.2426   0.04517   0.03770  -0.0153   0.0286   1.0000
  12.750   1.2522   0.04712   0.03986  -0.0143   0.0280   1.0000
  13.000   1.2605   0.04925   0.04218  -0.0132   0.0271   1.0000
  13.250   1.2656   0.05154   0.04466  -0.0124   0.0260   1.0000
  13.500   1.2700   0.05392   0.04718  -0.0117   0.0249   1.0000
  13.750   1.2728   0.05652   0.04992  -0.0111   0.0240   1.0000
  14.000   1.2759   0.05938   0.05294  -0.0105   0.0236   1.0000
  14.250   1.2772   0.06251   0.05623  -0.0101   0.0231   1.0000
  14.500   1.2767   0.06601   0.05990  -0.0098   0.0227   1.0000
  14.750   1.2726   0.07007   0.06415  -0.0097   0.0224   1.0000
  15.000   1.2644   0.07435   0.06866  -0.0101   0.0224   1.0000
  15.250   1.2528   0.07925   0.07379  -0.0108   0.0223   1.0000
  15.500   1.2388   0.08433   0.07911  -0.0122   0.0223   1.0000
  15.750   1.2231   0.08987   0.08487  -0.0141   0.0223   1.0000
  16.000   1.2056   0.09593   0.09116  -0.0166   0.0224   1.0000
  16.250   1.1847   0.10283   0.09832  -0.0202   0.0227   1.0000
  16.500   1.1602   0.11107   0.10682  -0.0247   0.0230   1.0000
  16.750   1.1210   0.12315   0.11925  -0.0325   0.0238   1.0000
  17.000   1.0727   0.13911   0.13552  -0.0432   0.0248   1.0000
  17.250   1.0155   0.16079   0.15737  -0.0573   0.0266   1.0000
  17.500   0.9873   0.17581   0.17236  -0.0654   0.0281   1.0000
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