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K3311 (original) (k3311-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: K3311 (original) (k3311-il)
Reynolds number: 500,000
Max Cl/Cd: 100.2 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-k3311-il-500000-n5.txt
Download as CSV file: xf-k3311-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: K3311  (original)                               
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4097   0.09221   0.08990  -0.0385   1.0000   0.0108
 -10.000  -0.4239   0.08527   0.08300  -0.0414   1.0000   0.0113
  -9.500  -0.5844   0.04022   0.03763  -0.0731   0.9883   0.0118
  -9.250  -0.5644   0.03775   0.03499  -0.0759   0.9822   0.0120
  -9.000  -0.5409   0.03601   0.03312  -0.0780   0.9765   0.0122
  -8.750  -0.5167   0.03452   0.03148  -0.0797   0.9702   0.0126
  -8.500  -0.4912   0.03167   0.02836  -0.0825   0.9635   0.0131
  -8.250  -0.4724   0.02681   0.02292  -0.0845   0.9517   0.0145
  -8.000  -0.4492   0.02301   0.01838  -0.0857   0.9384   0.0156
  -7.750  -0.4214   0.02153   0.01676  -0.0869   0.9258   0.0161
  -7.500  -0.3929   0.02097   0.01612  -0.0877   0.9149   0.0166
  -7.250  -0.3658   0.02035   0.01538  -0.0880   0.9036   0.0171
  -7.000  -0.3408   0.01954   0.01439  -0.0879   0.8911   0.0177
  -6.750  -0.3169   0.01853   0.01316  -0.0875   0.8786   0.0184
  -6.500  -0.2928   0.01763   0.01204  -0.0870   0.8665   0.0190
  -6.250  -0.2680   0.01698   0.01118  -0.0865   0.8550   0.0197
  -6.000  -0.2429   0.01651   0.01053  -0.0860   0.8434   0.0203
  -5.750  -0.2179   0.01602   0.00986  -0.0855   0.8307   0.0206
  -5.500  -0.1942   0.01494   0.00860  -0.0848   0.8172   0.0210
  -5.250  -0.1707   0.01391   0.00745  -0.0841   0.8029   0.0216
  -5.000  -0.1463   0.01332   0.00678  -0.0836   0.7894   0.0222
  -4.750  -0.1213   0.01289   0.00625  -0.0831   0.7771   0.0229
  -4.500  -0.0963   0.01244   0.00571  -0.0825   0.7661   0.0233
  -4.000  -0.0458   0.01167   0.00476  -0.0815   0.7451   0.0241
  -3.750  -0.0203   0.01133   0.00434  -0.0810   0.7346   0.0245
  -3.500   0.0051   0.01103   0.00396  -0.0805   0.7235   0.0249
  -3.250   0.0307   0.01076   0.00362  -0.0801   0.7125   0.0252
  -3.000   0.0566   0.01051   0.00330  -0.0796   0.7025   0.0257
  -2.750   0.0826   0.01032   0.00304  -0.0792   0.6936   0.0263
  -2.500   0.1086   0.01014   0.00279  -0.0789   0.6851   0.0267
  -2.250   0.1349   0.00997   0.00256  -0.0785   0.6772   0.0270
  -2.000   0.1612   0.00984   0.00235  -0.0782   0.6699   0.0273
  -1.750   0.1879   0.00972   0.00218  -0.0779   0.6632   0.0276
  -1.500   0.2143   0.00961   0.00199  -0.0776   0.6554   0.0286
  -1.250   0.2411   0.00951   0.00184  -0.0773   0.6470   0.0298
  -1.000   0.2676   0.00947   0.00173  -0.0770   0.6374   0.0313
  -0.750   0.2945   0.00940   0.00165  -0.0767   0.6270   0.0333
  -0.500   0.3215   0.00934   0.00158  -0.0765   0.6180   0.0362
  -0.250   0.3475   0.00914   0.00151  -0.0762   0.6088   0.0935
   0.000   0.3695   0.00826   0.00145  -0.0756   0.5992   0.3637
   0.250   0.3938   0.00795   0.00148  -0.0750   0.5888   0.4869
   0.500   0.4190   0.00785   0.00150  -0.0745   0.5784   0.5458
   1.000   0.4683   0.00761   0.00159  -0.0732   0.5595   0.6691
   1.250   0.4926   0.00755   0.00165  -0.0724   0.5506   0.7200
   1.500   0.5161   0.00743   0.00172  -0.0713   0.5416   0.7870
   1.750   0.5810   0.00719   0.00183  -0.0793   0.5276   0.9794
   2.000   0.6170   0.00733   0.00189  -0.0812   0.5157   1.0000
   2.500   0.6668   0.00756   0.00204  -0.0800   0.4985   1.0000
   3.000   0.7170   0.00780   0.00222  -0.0789   0.4837   1.0000
   3.250   0.7418   0.00794   0.00232  -0.0782   0.4759   1.0000
   3.500   0.7669   0.00806   0.00242  -0.0777   0.4656   1.0000
   3.750   0.7917   0.00822   0.00255  -0.0771   0.4541   1.0000
   4.000   0.8164   0.00838   0.00267  -0.0765   0.4420   1.0000
   4.250   0.8410   0.00854   0.00281  -0.0759   0.4305   1.0000
   4.500   0.8656   0.00871   0.00295  -0.0753   0.4165   1.0000
   4.750   0.8900   0.00890   0.00311  -0.0747   0.4006   1.0000
   5.000   0.9138   0.00912   0.00328  -0.0740   0.3809   1.0000
   5.250   0.9370   0.00939   0.00348  -0.0732   0.3614   1.0000
   5.750   0.9826   0.01000   0.00397  -0.0714   0.3227   1.0000
   6.000   1.0044   0.01038   0.00426  -0.0705   0.3007   1.0000
   6.250   1.0262   0.01076   0.00456  -0.0695   0.2763   1.0000
   6.500   1.0450   0.01135   0.00495  -0.0681   0.2360   1.0000
   6.750   1.0622   0.01206   0.00542  -0.0664   0.1936   1.0000
   7.000   1.0783   0.01283   0.00595  -0.0647   0.1478   1.0000
   7.250   1.0939   0.01362   0.00653  -0.0628   0.1102   1.0000
   7.500   1.1114   0.01425   0.00705  -0.0613   0.0895   1.0000
   7.750   1.1272   0.01497   0.00765  -0.0594   0.0618   1.0000
   8.000   1.1386   0.01595   0.00842  -0.0570   0.0308   1.0000
   8.250   1.1534   0.01666   0.00908  -0.0550   0.0202   1.0000
   8.500   1.1699   0.01722   0.00966  -0.0532   0.0166   1.0000
   8.750   1.1837   0.01781   0.01028  -0.0510   0.0143   1.0000
   9.000   1.1975   0.01837   0.01089  -0.0487   0.0132   1.0000
   9.250   1.2113   0.01893   0.01153  -0.0466   0.0122   1.0000
   9.500   1.2240   0.01957   0.01222  -0.0444   0.0112   1.0000
   9.750   1.2351   0.02033   0.01302  -0.0421   0.0104   1.0000
  10.000   1.2431   0.02129   0.01407  -0.0394   0.0097   1.0000
  10.250   1.2542   0.02210   0.01495  -0.0374   0.0094   1.0000
  10.500   1.2643   0.02300   0.01593  -0.0353   0.0091   1.0000
  10.750   1.2733   0.02400   0.01703  -0.0333   0.0087   1.0000
  11.000   1.2815   0.02511   0.01823  -0.0314   0.0084   1.0000
  11.250   1.2891   0.02633   0.01952  -0.0296   0.0081   1.0000
  11.500   1.2970   0.02757   0.02084  -0.0280   0.0077   1.0000
  11.750   1.3036   0.02897   0.02231  -0.0265   0.0074   1.0000
  12.000   1.3071   0.03070   0.02412  -0.0249   0.0071   1.0000
  12.250   1.3046   0.03306   0.02658  -0.0233   0.0068   1.0000
  12.500   1.3094   0.03489   0.02850  -0.0223   0.0067   1.0000
  12.750   1.3111   0.03709   0.03081  -0.0214   0.0066   1.0000
  13.000   1.3155   0.03911   0.03294  -0.0207   0.0064   1.0000
  13.250   1.3182   0.04138   0.03532  -0.0202   0.0063   1.0000
  13.500   1.3186   0.04396   0.03801  -0.0197   0.0061   1.0000
  13.750   1.3172   0.04680   0.04096  -0.0194   0.0060   1.0000
  14.000   1.3176   0.04952   0.04379  -0.0193   0.0059   1.0000
  14.250   1.3169   0.05246   0.04683  -0.0193   0.0058   1.0000
  14.500   1.3161   0.05552   0.05000  -0.0195   0.0055   1.0000
  14.750   1.3143   0.05880   0.05338  -0.0198   0.0054   1.0000
  15.000   1.3115   0.06228   0.05697  -0.0203   0.0054   1.0000
  15.250   1.3103   0.06570   0.06048  -0.0210   0.0052   1.0000
  15.500   1.3043   0.06980   0.06471  -0.0218   0.0053   1.0000
  15.750   1.3010   0.07367   0.06868  -0.0229   0.0052   1.0000
  16.000   1.2958   0.07788   0.07300  -0.0240   0.0052   1.0000
  16.250   1.2919   0.08208   0.07732  -0.0254   0.0050   1.0000
  16.500   1.2860   0.08662   0.08198  -0.0268   0.0050   1.0000
  16.750   1.2798   0.09131   0.08677  -0.0286   0.0049   1.0000
  17.000   1.2739   0.09606   0.09163  -0.0303   0.0049   1.0000
  17.250   1.2665   0.10114   0.09682  -0.0323   0.0048   1.0000
  17.500   1.2593   0.10635   0.10214  -0.0346   0.0048   1.0000
  17.750   1.2503   0.11185   0.10776  -0.0369   0.0047   1.0000
  18.000   1.2424   0.11734   0.11337  -0.0394   0.0047   1.0000
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