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E211 (10.96%) (e211-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: E211 (10.96%) (e211-il)
Reynolds number: 100,000
Max Cl/Cd: 57.56 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e211-il-100000-n5.txt
Download as CSV file: xf-e211-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4586   0.09026   0.08519  -0.0406   1.0000   0.0267
  -9.250  -0.4672   0.08534   0.08035  -0.0422   1.0000   0.0263
  -9.000  -0.4799   0.07973   0.07482  -0.0443   1.0000   0.0259
  -8.750  -0.4987   0.07268   0.06784  -0.0476   1.0000   0.0253
  -8.500  -0.5318   0.06563   0.06084  -0.0508   1.0000   0.0247
  -8.250  -0.5594   0.05945   0.05455  -0.0532   1.0000   0.0243
  -8.000  -0.5800   0.05342   0.04823  -0.0541   1.0000   0.0238
  -7.750  -0.5900   0.04791   0.04228  -0.0544   1.0000   0.0235
  -7.500  -0.5878   0.04380   0.03777  -0.0541   1.0000   0.0234
  -7.250  -0.5795   0.04037   0.03397  -0.0537   1.0000   0.0235
  -7.000  -0.5665   0.03804   0.03139  -0.0533   1.0000   0.0241
  -6.750  -0.5512   0.03597   0.02908  -0.0528   1.0000   0.0251
  -6.500  -0.5342   0.03368   0.02643  -0.0524   1.0000   0.0261
  -6.250  -0.5152   0.03130   0.02364  -0.0520   1.0000   0.0267
  -6.000  -0.4945   0.02910   0.02106  -0.0516   1.0000   0.0271
  -5.750  -0.4682   0.02718   0.01876  -0.0519   0.9988   0.0276
  -5.500  -0.4337   0.02545   0.01671  -0.0537   0.9953   0.0283
  -5.250  -0.3997   0.02405   0.01508  -0.0552   0.9913   0.0292
  -5.000  -0.3658   0.02271   0.01367  -0.0570   0.9871   0.0306
  -4.750  -0.3310   0.02180   0.01268  -0.0590   0.9828   0.0330
  -4.500  -0.2970   0.02105   0.01179  -0.0606   0.9772   0.0377
  -4.250  -0.2604   0.02009   0.01079  -0.0629   0.9730   0.0436
  -4.000  -0.2282   0.01920   0.00988  -0.0641   0.9665   0.0553
  -3.750  -0.1925   0.01830   0.00914  -0.0663   0.9614   0.0987
  -3.500  -0.1606   0.01734   0.00871  -0.0680   0.9549   0.1939
  -3.250  -0.1271   0.01632   0.00836  -0.0702   0.9490   0.3367
  -3.000  -0.0971   0.01577   0.00833  -0.0708   0.9416   0.4641
  -2.750  -0.0630   0.01563   0.00825  -0.0718   0.9349   0.5445
  -2.500  -0.0334   0.01555   0.00815  -0.0719   0.9257   0.5892
  -2.250   0.0021   0.01545   0.00801  -0.0731   0.9198   0.6237
  -2.000   0.0308   0.01536   0.00786  -0.0730   0.9098   0.6510
  -1.750   0.0621   0.01525   0.00772  -0.0733   0.9016   0.6741
  -1.500   0.0954   0.01510   0.00752  -0.0740   0.8940   0.6958
  -1.250   0.1249   0.01497   0.00735  -0.0739   0.8845   0.7142
  -1.000   0.1603   0.01478   0.00712  -0.0750   0.8780   0.7322
  -0.750   0.1896   0.01465   0.00697  -0.0749   0.8672   0.7486
  -0.500   0.2223   0.01450   0.00679  -0.0755   0.8581   0.7643
  -0.250   0.2576   0.01433   0.00659  -0.0766   0.8496   0.7789
   0.000   0.2886   0.01421   0.00644  -0.0770   0.8383   0.7925
   0.250   0.3215   0.01407   0.00628  -0.0777   0.8276   0.8056
   0.500   0.3564   0.01391   0.00610  -0.0788   0.8175   0.8185
   0.750   0.3891   0.01380   0.00597  -0.0794   0.8057   0.8316
   1.000   0.4199   0.01371   0.00588  -0.0797   0.7928   0.8457
   1.250   0.4504   0.01363   0.00580  -0.0800   0.7798   0.8606
   1.500   0.4806   0.01356   0.00575  -0.0801   0.7666   0.8776
   1.750   0.5114   0.01351   0.00571  -0.0805   0.7534   0.8976
   2.000   0.5447   0.01347   0.00568  -0.0813   0.7400   0.9217
   2.250   0.5832   0.01347   0.00570  -0.0834   0.7261   0.9539
   2.500   0.6205   0.01352   0.00573  -0.0855   0.7117   1.0000
   2.750   0.6510   0.01367   0.00584  -0.0862   0.6975   1.0000
   3.000   0.6805   0.01385   0.00598  -0.0867   0.6827   1.0000
   3.250   0.7089   0.01404   0.00616  -0.0869   0.6672   1.0000
   3.500   0.7365   0.01424   0.00634  -0.0868   0.6510   1.0000
   3.750   0.7635   0.01446   0.00654  -0.0867   0.6342   1.0000
   4.000   0.7900   0.01468   0.00678  -0.0864   0.6171   1.0000
   4.250   0.8161   0.01492   0.00700  -0.0860   0.5996   1.0000
   4.500   0.8414   0.01516   0.00725  -0.0854   0.5808   1.0000
   4.750   0.8656   0.01542   0.00753  -0.0847   0.5605   1.0000
   5.000   0.8897   0.01569   0.00782  -0.0839   0.5397   1.0000
   5.250   0.9128   0.01597   0.00814  -0.0829   0.5171   1.0000
   5.500   0.9355   0.01629   0.00844  -0.0819   0.4929   1.0000
   5.750   0.9572   0.01663   0.00879  -0.0807   0.4657   1.0000
   6.000   0.9780   0.01702   0.00918  -0.0793   0.4354   1.0000
   6.250   0.9978   0.01747   0.00960  -0.0778   0.4002   1.0000
   6.500   1.0158   0.01804   0.01007  -0.0761   0.3593   1.0000
   6.750   1.0323   0.01874   0.01061  -0.0742   0.3131   1.0000
   7.000   1.0473   0.01960   0.01128  -0.0722   0.2657   1.0000
   7.250   1.0611   0.02061   0.01210  -0.0701   0.2207   1.0000
   7.500   1.0741   0.02172   0.01299  -0.0681   0.1783   1.0000
   7.750   1.0863   0.02292   0.01395  -0.0660   0.1382   1.0000
   8.000   1.0981   0.02416   0.01496  -0.0639   0.1023   1.0000
   8.250   1.1104   0.02535   0.01601  -0.0619   0.0758   1.0000
   8.500   1.1204   0.02662   0.01718  -0.0595   0.0556   1.0000
   8.750   1.1292   0.02799   0.01851  -0.0569   0.0408   1.0000
   9.000   1.1360   0.02951   0.02008  -0.0541   0.0335   1.0000
   9.250   1.1433   0.03099   0.02166  -0.0514   0.0293   1.0000
   9.500   1.1473   0.03270   0.02343  -0.0486   0.0270   1.0000
   9.750   1.1536   0.03430   0.02522  -0.0461   0.0252   1.0000
  10.000   1.1597   0.03597   0.02705  -0.0438   0.0237   1.0000
  10.250   1.1655   0.03770   0.02889  -0.0417   0.0223   1.0000
  10.500   1.1697   0.03959   0.03086  -0.0398   0.0211   1.0000
  10.750   1.1741   0.04165   0.03306  -0.0380   0.0200   1.0000
  11.000   1.1804   0.04369   0.03530  -0.0364   0.0192   1.0000
  11.250   1.1860   0.04591   0.03773  -0.0350   0.0184   1.0000
  11.500   1.1912   0.04828   0.04028  -0.0337   0.0179   1.0000
  11.750   1.1958   0.05080   0.04299  -0.0326   0.0175   1.0000
  12.000   1.1993   0.05350   0.04588  -0.0316   0.0171   1.0000
  12.250   1.2013   0.05639   0.04896  -0.0308   0.0168   1.0000
  12.500   1.2016   0.05951   0.05229  -0.0302   0.0166   1.0000
  12.750   1.2000   0.06291   0.05589  -0.0298   0.0164   1.0000
  13.000   1.1964   0.06664   0.05983  -0.0298   0.0162   1.0000
  13.250   1.1906   0.07072   0.06414  -0.0302   0.0161   1.0000
  13.500   1.1826   0.07523   0.06887  -0.0310   0.0160   1.0000
  13.750   1.1724   0.08019   0.07407  -0.0323   0.0160   1.0000
  14.000   1.1597   0.08571   0.07983  -0.0343   0.0159   1.0000
  14.250   1.1448   0.09188   0.08625  -0.0371   0.0160   1.0000
  14.500   1.1274   0.09887   0.09350  -0.0407   0.0160   1.0000
  14.750   1.1068   0.10705   0.10193  -0.0455   0.0161   1.0000
  15.000   1.0819   0.11704   0.11219  -0.0519   0.0163   1.0000
  15.250   1.0470   0.13096   0.12639  -0.0613   0.0168   1.0000
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