Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

K3311 (original) (k3311-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: K3311 (original) (k3311-il)
Reynolds number: 50,000
Max Cl/Cd: 36.49 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-k3311-il-50000-n5.txt
Download as CSV file: xf-k3311-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3678   0.10643   0.09950  -0.0347   1.0000   0.1425
  -9.000  -0.3921   0.10493   0.09821  -0.0379   1.0000   0.1447
  -8.500  -0.3945   0.08924   0.08256  -0.0446   1.0000   0.0703
  -8.250  -0.3940   0.08614   0.07953  -0.0436   1.0000   0.0688
  -8.000  -0.4012   0.08294   0.07644  -0.0434   1.0000   0.0673
  -7.750  -0.4099   0.07917   0.07278  -0.0443   1.0000   0.0659
  -7.500  -0.4203   0.07510   0.06878  -0.0455   1.0000   0.0643
  -7.250  -0.4327   0.07085   0.06456  -0.0464   1.0000   0.0627
  -7.000  -0.4469   0.06612   0.05974  -0.0472   1.0000   0.0609
  -6.750  -0.4636   0.06076   0.05385  -0.0485   1.0000   0.0584
  -6.500  -0.4620   0.05760   0.05058  -0.0474   1.0000   0.0581
  -6.250  -0.4601   0.05434   0.04703  -0.0465   1.0000   0.0583
  -6.000  -0.4547   0.05147   0.04409  -0.0454   1.0000   0.0593
  -5.750  -0.4467   0.04938   0.04197  -0.0442   1.0000   0.0609
  -5.500  -0.4167   0.04549   0.03761  -0.0477   0.9924   0.0617
  -5.250  -0.3837   0.04160   0.03304  -0.0510   0.9843   0.0614
  -5.000  -0.3502   0.03849   0.02937  -0.0536   0.9760   0.0617
  -4.750  -0.3171   0.03608   0.02650  -0.0556   0.9674   0.0628
  -4.500  -0.2826   0.03418   0.02419  -0.0576   0.9591   0.0660
  -4.250  -0.2468   0.03235   0.02189  -0.0594   0.9510   0.0682
  -4.000  -0.2135   0.03077   0.01992  -0.0604   0.9421   0.0692
  -3.750  -0.1754   0.02939   0.01821  -0.0622   0.9351   0.0706
  -3.500  -0.1445   0.02824   0.01693  -0.0627   0.9256   0.0723
  -3.250  -0.1064   0.02715   0.01575  -0.0646   0.9192   0.0758
  -3.000  -0.0769   0.02646   0.01492  -0.0651   0.9089   0.0820
  -2.750  -0.0411   0.02566   0.01398  -0.0667   0.9013   0.0890
  -2.500  -0.0078   0.02496   0.01316  -0.0678   0.8926   0.0976
  -2.000   0.0578   0.02245   0.01170  -0.0708   0.8767   0.3079
  -1.750   0.0748   0.02143   0.01198  -0.0680   0.8670   0.6236
  -1.500   0.1549   0.02043   0.01177  -0.0744   0.8658   0.9871
  -1.250   0.1917   0.02043   0.01136  -0.0767   0.8573   1.0000
  -1.000   0.2192   0.02049   0.01111  -0.0771   0.8467   1.0000
  -0.750   0.2444   0.02063   0.01097  -0.0769   0.8353   1.0000
  -0.500   0.2733   0.02073   0.01083  -0.0773   0.8256   1.0000
  -0.250   0.3037   0.02081   0.01068  -0.0778   0.8162   1.0000
   0.000   0.3285   0.02101   0.01069  -0.0775   0.8050   1.0000
   0.250   0.3566   0.02116   0.01066  -0.0776   0.7954   1.0000
   0.500   0.3874   0.02125   0.01058  -0.0780   0.7866   1.0000
   0.750   0.4119   0.02149   0.01070  -0.0775   0.7756   1.0000
   1.000   0.4397   0.02167   0.01076  -0.0775   0.7661   1.0000
   1.250   0.4695   0.02177   0.01075  -0.0776   0.7570   1.0000
   1.500   0.4932   0.02206   0.01096  -0.0769   0.7456   1.0000
   1.750   0.5193   0.02228   0.01110  -0.0765   0.7351   1.0000
   2.000   0.5499   0.02235   0.01110  -0.0766   0.7262   1.0000
   2.250   0.5724   0.02268   0.01140  -0.0758   0.7144   1.0000
   2.500   0.5968   0.02297   0.01166  -0.0751   0.7036   1.0000
   2.750   0.6250   0.02314   0.01181  -0.0749   0.6945   1.0000
   3.000   0.6512   0.02339   0.01205  -0.0745   0.6846   1.0000
   3.250   0.6750   0.02375   0.01243  -0.0738   0.6740   1.0000
   3.500   0.7022   0.02399   0.01269  -0.0735   0.6647   1.0000
   3.750   0.7288   0.02426   0.01299  -0.0730   0.6549   1.0000
   4.000   0.7508   0.02472   0.01351  -0.0721   0.6435   1.0000
   4.250   0.7744   0.02511   0.01399  -0.0713   0.6326   1.0000
   4.500   0.8005   0.02537   0.01430  -0.0708   0.6221   1.0000
   4.750   0.8244   0.02569   0.01470  -0.0699   0.6106   1.0000
   5.000   0.8455   0.02612   0.01525  -0.0688   0.5979   1.0000
   5.250   0.8675   0.02649   0.01574  -0.0677   0.5855   1.0000
   5.500   0.8906   0.02683   0.01618  -0.0667   0.5736   1.0000
   5.750   0.9155   0.02708   0.01654  -0.0659   0.5620   1.0000
   6.000   0.9428   0.02722   0.01682  -0.0653   0.5510   1.0000
   6.250   0.9636   0.02770   0.01744  -0.0641   0.5377   1.0000
   6.500   0.9848   0.02815   0.01806  -0.0629   0.5244   1.0000
   6.750   1.0064   0.02859   0.01865  -0.0617   0.5107   1.0000
   7.000   1.0280   0.02897   0.01922  -0.0605   0.4962   1.0000
   7.250   1.0495   0.02921   0.01959  -0.0590   0.4795   1.0000
   7.500   1.0710   0.02935   0.01982  -0.0574   0.4616   1.0000
   7.750   1.0860   0.02986   0.02050  -0.0553   0.4423   1.0000
   8.000   1.1011   0.03038   0.02120  -0.0532   0.4234   1.0000
   8.250   1.1173   0.03087   0.02189  -0.0512   0.4052   1.0000
   8.500   1.1343   0.03131   0.02246  -0.0493   0.3870   1.0000
   8.750   1.1455   0.03208   0.02343  -0.0469   0.3672   1.0000
   9.000   1.1558   0.03258   0.02396  -0.0441   0.3433   1.0000
   9.250   1.1535   0.03345   0.02473  -0.0400   0.3117   1.0000
   9.500   1.1459   0.03473   0.02590  -0.0357   0.2771   1.0000
   9.750   1.1379   0.03642   0.02740  -0.0322   0.2414   1.0000
  10.000   1.1314   0.03851   0.02935  -0.0296   0.2078   1.0000
  10.250   1.1248   0.04097   0.03174  -0.0275   0.1754   1.0000
  10.500   1.1165   0.04389   0.03449  -0.0259   0.1452   1.0000
  10.750   1.1065   0.04728   0.03770  -0.0248   0.1200   1.0000
  11.000   1.0965   0.05095   0.04121  -0.0240   0.1024   1.0000
  11.250   1.0869   0.05481   0.04498  -0.0235   0.0886   1.0000
  11.500   1.0804   0.05852   0.04869  -0.0231   0.0772   1.0000
  11.750   1.0764   0.06204   0.05225  -0.0229   0.0690   1.0000
  12.000   1.0710   0.06578   0.05595  -0.0229   0.0633   1.0000
  12.250   1.0708   0.06902   0.05935  -0.0227   0.0580   1.0000
  12.500   1.0702   0.07231   0.06270  -0.0226   0.0547   1.0000
  12.750   1.0703   0.07556   0.06597  -0.0225   0.0519   1.0000
  13.000   1.0743   0.07851   0.06916  -0.0221   0.0487   1.0000
  13.250   1.0763   0.08175   0.07256  -0.0222   0.0459   1.0000
  13.500   1.0778   0.08503   0.07594  -0.0224   0.0436   1.0000
  13.750   1.0827   0.08791   0.07884  -0.0220   0.0418   1.0000
  14.000   1.0866   0.09145   0.08271  -0.0221   0.0407   1.0000
  14.250   1.0864   0.09569   0.08726  -0.0227   0.0399   1.0000
  14.500   1.0813   0.10075   0.09261  -0.0242   0.0391   1.0000
  14.750   1.0728   0.10650   0.09863  -0.0265   0.0386   1.0000
  15.000   1.0614   0.11299   0.10537  -0.0295   0.0384   1.0000
  15.250   1.0467   0.12046   0.11308  -0.0334   0.0384   1.0000
  15.500   1.0291   0.12909   0.12192  -0.0383   0.0386   1.0000
  15.750   1.0090   0.13905   0.13206  -0.0442   0.0391   1.0000
<< Back to K3311 (original) (k3311-il)

Polar data table (+)

Polar graphs


<< Back to K3311 (original) (k3311-il)