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K3311 (smoothed) (k3311sm-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: K3311 (smoothed) (k3311sm-il)
Reynolds number: 50,000
Max Cl/Cd: 36.38 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-k3311sm-il-50000-n5.txt
Download as CSV file: xf-k3311sm-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3567   0.11319   0.10605  -0.0338   1.0000   0.1154
  -9.500  -0.3579   0.11032   0.10326  -0.0348   1.0000   0.1192
  -9.250  -0.3727   0.10232   0.09530  -0.0419   1.0000   0.0655
  -9.000  -0.3646   0.09891   0.09193  -0.0408   1.0000   0.0638
  -8.750  -0.3646   0.09555   0.08864  -0.0412   1.0000   0.0628
  -8.500  -0.3666   0.09221   0.08539  -0.0415   1.0000   0.0615
  -8.000  -0.4118   0.08155   0.07501  -0.0500   1.0000   0.0531
  -7.750  -0.4174   0.07815   0.07167  -0.0498   1.0000   0.0529
  -7.500  -0.4235   0.07490   0.06846  -0.0493   1.0000   0.0527
  -7.250  -0.4294   0.07175   0.06534  -0.0485   1.0000   0.0524
  -7.000  -0.4368   0.06846   0.06202  -0.0479   1.0000   0.0523
  -6.750  -0.4420   0.06529   0.05880  -0.0469   1.0000   0.0521
  -6.500  -0.4455   0.06209   0.05552  -0.0460   1.0000   0.0518
  -6.250  -0.4471   0.05881   0.05209  -0.0451   1.0000   0.0516
  -6.000  -0.4459   0.05553   0.04863  -0.0443   1.0000   0.0513
  -5.750  -0.4420   0.05228   0.04513  -0.0435   1.0000   0.0510
  -5.500  -0.4168   0.04777   0.04012  -0.0468   0.9934   0.0509
  -5.250  -0.3858   0.04356   0.03527  -0.0502   0.9851   0.0514
  -5.000  -0.3541   0.04016   0.03112  -0.0527   0.9764   0.0534
  -4.750  -0.3220   0.03749   0.02825  -0.0552   0.9692   0.0565
  -4.500  -0.2897   0.03504   0.02535  -0.0568   0.9606   0.0583
  -4.250  -0.2556   0.03289   0.02273  -0.0583   0.9528   0.0608
  -4.000  -0.2199   0.03127   0.02053  -0.0597   0.9448   0.0659
  -3.750  -0.1880   0.02958   0.01875  -0.0608   0.9365   0.0701
  -3.500  -0.1518   0.02824   0.01721  -0.0621   0.9293   0.0753
  -3.250  -0.1210   0.02717   0.01602  -0.0627   0.9201   0.0839
  -3.000  -0.0823   0.02614   0.01477  -0.0645   0.9136   0.0943
  -2.750  -0.0528   0.02524   0.01385  -0.0652   0.9035   0.1108
  -2.500  -0.0173   0.02416   0.01287  -0.0669   0.8960   0.1428
  -2.250   0.0110   0.02228   0.01231  -0.0679   0.8874   0.3709
  -2.000   0.0331   0.02153   0.01239  -0.0659   0.8783   0.6098
  -1.750   0.0594   0.02089   0.01240  -0.0630   0.8712   0.8104
  -1.500   0.1596   0.02048   0.01173  -0.0758   0.8705   1.0000
  -1.250   0.1845   0.02052   0.01141  -0.0759   0.8585   1.0000
  -1.000   0.2121   0.02058   0.01117  -0.0763   0.8475   1.0000
  -0.750   0.2462   0.02057   0.01086  -0.0776   0.8392   1.0000
  -0.500   0.2716   0.02071   0.01075  -0.0774   0.8276   1.0000
  -0.250   0.2978   0.02086   0.01070  -0.0773   0.8166   1.0000
   0.000   0.3281   0.02095   0.01058  -0.0778   0.8074   1.0000
   0.250   0.3569   0.02108   0.01052  -0.0779   0.7976   1.0000
   0.500   0.3819   0.02129   0.01059  -0.0775   0.7865   1.0000
   0.750   0.4102   0.02144   0.01060  -0.0776   0.7770   1.0000
   1.000   0.4396   0.02156   0.01060  -0.0777   0.7677   1.0000
   1.250   0.4635   0.02184   0.01078  -0.0771   0.7566   1.0000
   1.500   0.4904   0.02204   0.01089  -0.0768   0.7468   1.0000
   1.750   0.5199   0.02217   0.01093  -0.0769   0.7380   1.0000
   2.000   0.5430   0.02249   0.01122  -0.0761   0.7268   1.0000
   2.250   0.5687   0.02275   0.01143  -0.0757   0.7167   1.0000
   2.500   0.5986   0.02287   0.01149  -0.0757   0.7081   1.0000
   2.750   0.6209   0.02325   0.01189  -0.0748   0.6967   1.0000
   3.000   0.6454   0.02356   0.01219  -0.0742   0.6862   1.0000
   3.250   0.6750   0.02368   0.01229  -0.0741   0.6775   1.0000
   3.500   0.6978   0.02406   0.01270  -0.0732   0.6661   1.0000
   3.750   0.7208   0.02444   0.01314  -0.0724   0.6549   1.0000
   4.000   0.7465   0.02471   0.01344  -0.0718   0.6447   1.0000
   4.250   0.7741   0.02489   0.01366  -0.0715   0.6349   1.0000
   4.500   0.7956   0.02534   0.01418  -0.0704   0.6229   1.0000
   4.750   0.8184   0.02573   0.01468  -0.0695   0.6113   1.0000
   5.000   0.8432   0.02603   0.01506  -0.0687   0.6003   1.0000
   5.250   0.8711   0.02618   0.01526  -0.0683   0.5899   1.0000
   5.500   0.8924   0.02661   0.01580  -0.0672   0.5771   1.0000
   5.750   0.9139   0.02703   0.01638  -0.0660   0.5644   1.0000
   6.000   0.9359   0.02742   0.01689  -0.0649   0.5514   1.0000
   6.250   0.9581   0.02779   0.01739  -0.0638   0.5384   1.0000
   6.500   0.9804   0.02814   0.01787  -0.0626   0.5250   1.0000
   6.750   1.0023   0.02850   0.01839  -0.0614   0.5111   1.0000
   7.000   1.0236   0.02886   0.01890  -0.0601   0.4966   1.0000
   7.250   1.0441   0.02924   0.01943  -0.0587   0.4814   1.0000
   7.500   1.0638   0.02962   0.01996  -0.0571   0.4655   1.0000
   7.750   1.0832   0.02999   0.02051  -0.0555   0.4488   1.0000
   8.000   1.1026   0.03031   0.02096  -0.0538   0.4315   1.0000
   8.250   1.1185   0.03079   0.02157  -0.0518   0.4127   1.0000
   8.500   1.1315   0.03137   0.02230  -0.0494   0.3924   1.0000
   8.750   1.1451   0.03180   0.02279  -0.0470   0.3708   1.0000
   9.000   1.1518   0.03253   0.02364  -0.0439   0.3464   1.0000
   9.250   1.1551   0.03335   0.02448  -0.0406   0.3202   1.0000
   9.500   1.1546   0.03437   0.02545  -0.0369   0.2935   1.0000
   9.750   1.1524   0.03568   0.02670  -0.0335   0.2661   1.0000
  10.000   1.1492   0.03733   0.02828  -0.0306   0.2390   1.0000
  10.250   1.1447   0.03932   0.03020  -0.0281   0.2123   1.0000
  10.500   1.1387   0.04170   0.03246  -0.0260   0.1865   1.0000
  10.750   1.1321   0.04443   0.03513  -0.0244   0.1620   1.0000
  11.000   1.1249   0.04748   0.03808  -0.0231   0.1402   1.0000
  11.250   1.1175   0.05078   0.04128  -0.0223   0.1227   1.0000
  11.500   1.1105   0.05423   0.04466  -0.0216   0.1086   1.0000
  11.750   1.1050   0.05769   0.04812  -0.0212   0.0967   1.0000
  12.000   1.1012   0.06111   0.05154  -0.0208   0.0871   1.0000
  12.250   1.0979   0.06449   0.05487  -0.0206   0.0806   1.0000
  12.500   1.0976   0.06771   0.05823  -0.0203   0.0734   1.0000
  12.750   1.0962   0.07103   0.06153  -0.0202   0.0682   1.0000
  13.000   1.0988   0.07410   0.06481  -0.0199   0.0633   1.0000
  13.250   1.1011   0.07712   0.06787  -0.0197   0.0597   1.0000
  13.500   1.1047   0.08017   0.07104  -0.0194   0.0564   1.0000
  13.750   1.1049   0.08388   0.07505  -0.0198   0.0531   1.0000
  14.000   1.1048   0.08757   0.07890  -0.0203   0.0505   1.0000
  14.250   1.1076   0.09087   0.08229  -0.0204   0.0485   1.0000
  14.500   1.1128   0.09413   0.08563  -0.0203   0.0469   1.0000
  14.750   1.1045   0.09959   0.09148  -0.0221   0.0462   1.0000
  15.000   1.0931   0.10570   0.09788  -0.0246   0.0457   1.0000
  15.250   1.0789   0.11258   0.10502  -0.0279   0.0454   1.0000
  15.500   1.0620   0.12038   0.11302  -0.0320   0.0453   1.0000
  15.750   1.0430   0.12915   0.12199  -0.0370   0.0455   1.0000
  16.000   1.0220   0.13911   0.13211  -0.0430   0.0458   1.0000
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