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E211 (10.96%) (e211-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E211 (10.96%) (e211-il)
Reynolds number: 50,000
Max Cl/Cd: 39.19 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e211-il-50000-n5.txt
Download as CSV file: xf-e211-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E211  (10.96%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4473   0.10493   0.09761  -0.0406   1.0000   0.0489
  -9.750  -0.4466   0.10129   0.09402  -0.0409   1.0000   0.0484
  -9.500  -0.4481   0.09746   0.09025  -0.0416   1.0000   0.0479
  -9.250  -0.4516   0.09343   0.08630  -0.0424   1.0000   0.0474
  -9.000  -0.4576   0.08911   0.08207  -0.0436   1.0000   0.0469
  -8.750  -0.4651   0.08476   0.07781  -0.0448   1.0000   0.0463
  -8.500  -0.4775   0.07982   0.07296  -0.0466   1.0000   0.0457
  -8.250  -0.4960   0.07509   0.06833  -0.0482   1.0000   0.0452
  -8.000  -0.5123   0.07018   0.06344  -0.0502   1.0000   0.0446
  -7.750  -0.5259   0.06548   0.05868  -0.0514   1.0000   0.0441
  -7.500  -0.5347   0.06097   0.05402  -0.0521   1.0000   0.0437
  -7.250  -0.5387   0.05656   0.04937  -0.0525   1.0000   0.0434
  -7.000  -0.5374   0.05225   0.04475  -0.0529   1.0000   0.0432
  -6.750  -0.5310   0.04821   0.04033  -0.0530   1.0000   0.0432
  -6.500  -0.5200   0.04451   0.03620  -0.0530   1.0000   0.0435
  -6.250  -0.5052   0.04133   0.03258  -0.0529   1.0000   0.0444
  -6.000  -0.4877   0.03852   0.02925  -0.0526   1.0000   0.0462
  -5.750  -0.4678   0.03600   0.02619  -0.0522   1.0000   0.0483
  -5.500  -0.4472   0.03375   0.02359  -0.0516   1.0000   0.0501
  -5.250  -0.4267   0.03193   0.02162  -0.0509   1.0000   0.0519
  -5.000  -0.4056   0.03038   0.01991  -0.0499   1.0000   0.0543
  -4.750  -0.3842   0.02903   0.01836  -0.0488   1.0000   0.0574
  -4.500  -0.3627   0.02783   0.01688  -0.0475   1.0000   0.0620
  -4.250  -0.3419   0.02676   0.01583  -0.0468   1.0000   0.0711
  -4.000  -0.3203   0.02569   0.01473  -0.0462   1.0000   0.0839
  -3.750  -0.2980   0.02451   0.01366  -0.0460   1.0000   0.1125
  -3.500  -0.2742   0.02320   0.01283  -0.0467   1.0000   0.1852
  -3.250  -0.2492   0.02183   0.01211  -0.0476   1.0000   0.3028
  -3.000  -0.2302   0.02117   0.01227  -0.0463   1.0000   0.4542
  -2.750  -0.2068   0.02135   0.01261  -0.0452   0.9965   0.5648
  -2.500  -0.1739   0.02172   0.01291  -0.0458   0.9874   0.6357
  -2.250  -0.1436   0.02201   0.01309  -0.0457   0.9778   0.6844
  -2.000  -0.1139   0.02222   0.01319  -0.0456   0.9682   0.7254
  -1.750  -0.0846   0.02236   0.01323  -0.0453   0.9586   0.7597
  -1.500  -0.0572   0.02237   0.01312  -0.0447   0.9480   0.7910
  -1.250  -0.0310   0.02230   0.01296  -0.0440   0.9369   0.8204
  -1.000  -0.0041   0.02219   0.01277  -0.0436   0.9259   0.8492
  -0.750   0.0262   0.02206   0.01255  -0.0438   0.9158   0.8785
  -0.500   0.0645   0.02193   0.01232  -0.0457   0.9069   0.9085
  -0.250   0.1069   0.02182   0.01212  -0.0489   0.8965   0.9404
   0.000   0.1582   0.02169   0.01186  -0.0541   0.8870   0.9819
   0.250   0.2003   0.02162   0.01164  -0.0578   0.8779   1.0000
   0.500   0.2337   0.02164   0.01154  -0.0597   0.8659   1.0000
   0.750   0.2687   0.02169   0.01147  -0.0618   0.8547   1.0000
   1.000   0.3078   0.02168   0.01136  -0.0644   0.8456   1.0000
   1.250   0.3455   0.02168   0.01129  -0.0666   0.8357   1.0000
   1.500   0.3792   0.02177   0.01132  -0.0681   0.8242   1.0000
   1.750   0.4153   0.02183   0.01134  -0.0698   0.8137   1.0000
   2.000   0.4559   0.02179   0.01129  -0.0722   0.8050   1.0000
   2.500   0.5199   0.02205   0.01156  -0.0740   0.7806   1.0000
   2.750   0.5537   0.02215   0.01170  -0.0751   0.7690   1.0000
   3.000   0.5899   0.02218   0.01176  -0.0764   0.7583   1.0000
   3.250   0.6240   0.02226   0.01190  -0.0774   0.7464   1.0000
   3.500   0.6545   0.02245   0.01217  -0.0778   0.7329   1.0000
   3.750   0.6851   0.02263   0.01242  -0.0781   0.7192   1.0000
   4.000   0.7157   0.02280   0.01267  -0.0784   0.7050   1.0000
   4.250   0.7461   0.02296   0.01292  -0.0785   0.6900   1.0000
   4.500   0.7764   0.02311   0.01320  -0.0786   0.6743   1.0000
   4.750   0.8067   0.02324   0.01342  -0.0785   0.6577   1.0000
   5.000   0.8333   0.02346   0.01375  -0.0779   0.6394   1.0000
   5.250   0.8583   0.02372   0.01416  -0.0771   0.6196   1.0000
   5.500   0.8856   0.02387   0.01441  -0.0764   0.5992   1.0000
   5.750   0.9084   0.02414   0.01480  -0.0751   0.5764   1.0000
   6.000   0.9334   0.02430   0.01505  -0.0739   0.5527   1.0000
   6.250   0.9532   0.02462   0.01552  -0.0721   0.5259   1.0000
   6.500   0.9726   0.02494   0.01594  -0.0702   0.4971   1.0000
   6.750   0.9910   0.02529   0.01635  -0.0682   0.4654   1.0000
   7.000   1.0068   0.02577   0.01688  -0.0658   0.4297   1.0000
   7.250   1.0212   0.02634   0.01742  -0.0633   0.3906   1.0000
   7.500   1.0330   0.02711   0.01811  -0.0606   0.3472   1.0000
   7.750   1.0424   0.02813   0.01903  -0.0578   0.3015   1.0000
   8.000   1.0498   0.02943   0.02012  -0.0549   0.2583   1.0000
   8.250   1.0551   0.03091   0.02141  -0.0520   0.2209   1.0000
   8.500   1.0594   0.03259   0.02292  -0.0492   0.1898   1.0000
   8.750   1.0637   0.03440   0.02463  -0.0466   0.1622   1.0000
   9.000   1.0680   0.03635   0.02651  -0.0441   0.1374   1.0000
   9.250   1.0701   0.03844   0.02851  -0.0418   0.1147   1.0000
   9.500   1.0705   0.04063   0.03059  -0.0397   0.0949   1.0000
   9.750   1.0720   0.04294   0.03292  -0.0378   0.0782   1.0000
  10.000   1.0740   0.04540   0.03538  -0.0362   0.0667   1.0000
  10.250   1.0775   0.04788   0.03793  -0.0347   0.0580   1.0000
  10.500   1.0862   0.05036   0.04060  -0.0332   0.0521   1.0000
  10.750   1.0935   0.05283   0.04317  -0.0320   0.0477   1.0000
  11.000   1.1036   0.05541   0.04590  -0.0308   0.0441   1.0000
  11.250   1.1123   0.05812   0.04892  -0.0298   0.0406   1.0000
  11.500   1.1176   0.06094   0.05192  -0.0291   0.0384   1.0000
  11.750   1.1223   0.06392   0.05501  -0.0284   0.0367   1.0000
  12.000   1.1279   0.06740   0.05866  -0.0278   0.0357   1.0000
  12.250   1.1259   0.07149   0.06319  -0.0275   0.0351   1.0000
  12.500   1.1192   0.07605   0.06809  -0.0277   0.0347   1.0000
  12.750   1.1083   0.08110   0.07347  -0.0287   0.0345   1.0000
  13.000   1.0942   0.08675   0.07940  -0.0304   0.0344   1.0000
  13.250   1.0778   0.09297   0.08588  -0.0329   0.0344   1.0000
  13.500   1.0594   0.09990   0.09304  -0.0363   0.0345   1.0000
  13.750   1.0400   0.10754   0.10087  -0.0407   0.0347   1.0000
  14.000   1.0200   0.11599   0.10945  -0.0458   0.0349   1.0000
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