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K3311 (smoothed) (k3311sm-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: K3311 (smoothed) (k3311sm-il)
Reynolds number: 50,000
Max Cl/Cd: 33.89 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-k3311sm-il-50000.txt
Download as CSV file: xf-k3311sm-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3715   0.12528   0.11816  -0.0282   1.0000   0.1952
 -10.000  -0.3515   0.11994   0.11282  -0.0270   1.0000   0.2026
  -9.750  -0.3662   0.11944   0.11245  -0.0285   1.0000   0.2100
  -9.500  -0.3482   0.11465   0.10766  -0.0272   1.0000   0.2220
  -9.250  -0.3425   0.11138   0.10445  -0.0268   1.0000   0.2314
  -9.000  -0.3599   0.11100   0.10422  -0.0277   1.0000   0.2397
  -8.750  -0.3467   0.10705   0.10027  -0.0264   1.0000   0.2533
  -8.500  -0.3353   0.10333   0.09660  -0.0253   1.0000   0.2648
  -8.250  -0.3335   0.10053   0.09388  -0.0245   1.0000   0.2755
  -8.000  -0.3401   0.09853   0.09200  -0.0238   1.0000   0.2870
  -7.750  -0.3579   0.09798   0.09161  -0.0225   1.0000   0.2992
  -7.500  -0.3512   0.09489   0.08859  -0.0208   1.0000   0.3136
  -7.250  -0.3479   0.09215   0.08594  -0.0188   1.0000   0.3281
  -7.000  -0.3503   0.08990   0.08379  -0.0165   1.0000   0.3430
  -6.750  -0.3540   0.08783   0.08184  -0.0138   1.0000   0.3580
  -6.500  -0.3630   0.08621   0.08037  -0.0104   1.0000   0.3732
  -6.250  -0.3401   0.08223   0.07636  -0.0082   1.0000   0.3990
  -6.000  -0.3571   0.08136   0.07567  -0.0036   1.0000   0.4164
  -5.750  -0.3768   0.08063   0.07512   0.0015   1.0000   0.4324
  -5.500  -0.3580   0.07710   0.07158   0.0040   1.0000   0.4583
  -5.250  -0.3871   0.07710   0.07176   0.0103   1.0000   0.4771
  -4.500  -0.4175   0.05071   0.04400  -0.0364   1.0000   0.1681
  -4.250  -0.3968   0.04618   0.03886  -0.0379   1.0000   0.1500
  -4.000  -0.3783   0.04289   0.03526  -0.0380   1.0000   0.1447
  -3.750  -0.3543   0.03966   0.03116  -0.0386   1.0000   0.1357
  -3.500  -0.3334   0.03718   0.02831  -0.0382   1.0000   0.1328
  -3.250  -0.3116   0.03510   0.02578  -0.0377   1.0000   0.1319
  -3.000  -0.2903   0.03361   0.02377  -0.0370   1.0000   0.1356
  -2.750  -0.2691   0.03213   0.02196  -0.0363   1.0000   0.1392
  -2.500  -0.2485   0.03089   0.02059  -0.0355   1.0000   0.1429
  -2.250  -0.2276   0.03003   0.01948  -0.0346   1.0000   0.1503
  -2.000  -0.2069   0.02919   0.01864  -0.0339   1.0000   0.1624
  -1.750  -0.1866   0.02848   0.01788  -0.0329   1.0000   0.1753
  -1.500  -0.1601   0.02788   0.01734  -0.0333   0.9985   0.2062
  -1.250  -0.1116   0.02394   0.01698  -0.0339   0.9923   1.0000
  -1.000  -0.0643   0.02497   0.01710  -0.0386   0.9806   1.0000
  -0.750  -0.0197   0.02597   0.01752  -0.0430   0.9693   1.0000
  -0.500   0.0221   0.02689   0.01800  -0.0469   0.9574   1.0000
  -0.250   0.0579   0.02768   0.01845  -0.0497   0.9453   1.0000
   0.000   0.0929   0.02850   0.01896  -0.0522   0.9334   1.0000
   0.250   0.1284   0.02934   0.01955  -0.0547   0.9218   1.0000
   0.500   0.1661   0.03021   0.02019  -0.0576   0.9104   1.0000
   0.750   0.2034   0.03105   0.02083  -0.0602   0.8991   1.0000
   1.000   0.2306   0.03182   0.02144  -0.0612   0.8868   1.0000
   1.250   0.2583   0.03265   0.02214  -0.0622   0.8751   1.0000
   1.500   0.2891   0.03350   0.02286  -0.0636   0.8635   1.0000
   1.750   0.3245   0.03434   0.02360  -0.0657   0.8525   1.0000
   2.000   0.3562   0.03516   0.02434  -0.0671   0.8408   1.0000
   2.250   0.3778   0.03607   0.02519  -0.0670   0.8286   1.0000
   2.500   0.4021   0.03699   0.02607  -0.0673   0.8166   1.0000
   2.750   0.4296   0.03791   0.02695  -0.0680   0.8050   1.0000
   3.000   0.4629   0.03873   0.02777  -0.0694   0.7935   1.0000
   3.250   0.4941   0.03955   0.02858  -0.0704   0.7818   1.0000
   3.500   0.5125   0.04062   0.02966  -0.0698   0.7690   1.0000
   3.750   0.5321   0.04173   0.03078  -0.0694   0.7565   1.0000
   4.000   0.5547   0.04278   0.03187  -0.0693   0.7439   1.0000
   4.250   0.5799   0.04377   0.03290  -0.0694   0.7314   1.0000
   4.500   0.6089   0.04464   0.03383  -0.0698   0.7192   1.0000
   4.750   0.6493   0.04506   0.03438  -0.0712   0.7076   1.0000
   5.000   0.6647   0.04634   0.03572  -0.0702   0.6939   1.0000
   5.250   0.6825   0.04757   0.03701  -0.0693   0.6801   1.0000
   5.500   0.7008   0.04879   0.03831  -0.0685   0.6663   1.0000
   5.750   0.7195   0.05001   0.03963  -0.0678   0.6523   1.0000
   6.000   0.7394   0.05117   0.04092  -0.0670   0.6381   1.0000
   6.250   0.7588   0.05237   0.04223  -0.0662   0.6239   1.0000
   6.500   0.7789   0.05350   0.04348  -0.0654   0.6094   1.0000
   6.750   0.7992   0.05462   0.04473  -0.0645   0.5948   1.0000
   7.000   0.8212   0.05555   0.04584  -0.0635   0.5798   1.0000
   7.250   0.8442   0.05637   0.04682  -0.0625   0.5647   1.0000
   7.500   0.8706   0.05681   0.04745  -0.0614   0.5495   1.0000
   7.750   0.9039   0.05649   0.04735  -0.0601   0.5341   1.0000
   8.000   0.9673   0.05322   0.04449  -0.0592   0.5184   1.0000
   8.250   1.0139   0.05136   0.04293  -0.0581   0.5007   1.0000
   8.500   1.0032   0.05424   0.04589  -0.0549   0.4832   1.0000
   8.750   1.1233   0.04498   0.03722  -0.0554   0.4545   1.0000
   9.000   1.1965   0.03884   0.03118  -0.0542   0.4130   1.0000
   9.250   1.2236   0.03645   0.02865  -0.0508   0.3712   1.0000
   9.500   1.2283   0.03624   0.02836  -0.0462   0.3319   1.0000
   9.750   1.2262   0.03670   0.02857  -0.0411   0.2895   1.0000
  10.000   1.2175   0.03809   0.02961  -0.0359   0.2473   1.0000
  10.250   1.2076   0.04011   0.03124  -0.0310   0.2110   1.0000
  10.500   1.2019   0.04253   0.03338  -0.0271   0.1806   1.0000
  10.750   1.2061   0.04519   0.03583  -0.0245   0.1551   1.0000
  11.000   1.2175   0.04784   0.03834  -0.0227   0.1357   1.0000
  11.250   1.2473   0.05116   0.04150  -0.0228   0.1190   1.0000
  11.500   1.2506   0.05419   0.04493  -0.0205   0.1120   1.0000
  11.750   1.2642   0.05758   0.04841  -0.0195   0.1043   1.0000
  12.000   1.2597   0.06097   0.05220  -0.0171   0.1012   1.0000
  12.250   1.2584   0.06473   0.05627  -0.0153   0.0988   1.0000
  12.500   1.2609   0.06869   0.06043  -0.0140   0.0964   1.0000
  12.750   1.2669   0.07343   0.06526  -0.0134   0.0937   1.0000
  13.000   1.2470   0.07757   0.06970  -0.0118   0.0936   1.0000
  13.250   1.2251   0.08223   0.07462  -0.0111   0.0937   1.0000
  13.500   1.2028   0.08736   0.07998  -0.0112   0.0938   1.0000
  13.750   1.1028   0.09915   0.09233  -0.0183   0.1025   1.0000
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