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E226 (10.19%) (e226-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: E226 (10.19%) (e226-il)
Reynolds number: 200,000
Max Cl/Cd: 55.34 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e226-il-200000-n5.txt
Download as CSV file: xf-e226-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E226  (10.19%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.6641   0.08685   0.08322  -0.0170   1.0000   0.0133
 -11.250  -0.7300   0.06452   0.06047  -0.0351   1.0000   0.0125
 -11.000  -0.7461   0.05837   0.05418  -0.0401   1.0000   0.0125
 -10.750  -0.7654   0.05309   0.04873  -0.0435   1.0000   0.0125
 -10.500  -0.7807   0.04931   0.04478  -0.0443   1.0000   0.0124
 -10.250  -0.7959   0.04622   0.04148  -0.0428   1.0000   0.0124
 -10.000  -0.8039   0.04326   0.03826  -0.0411   1.0000   0.0124
  -9.750  -0.8061   0.04029   0.03498  -0.0395   1.0000   0.0124
  -9.500  -0.8043   0.03745   0.03179  -0.0379   1.0000   0.0124
  -9.250  -0.7970   0.03497   0.02900  -0.0363   1.0000   0.0125
  -9.000  -0.7873   0.03265   0.02635  -0.0348   1.0000   0.0125
  -8.750  -0.7762   0.03011   0.02353  -0.0332   1.0000   0.0127
  -8.500  -0.7619   0.02809   0.02131  -0.0318   1.0000   0.0129
  -8.250  -0.7458   0.02643   0.01945  -0.0305   1.0000   0.0131
  -8.000  -0.7288   0.02498   0.01784  -0.0291   1.0000   0.0133
  -7.750  -0.7115   0.02378   0.01654  -0.0277   1.0000   0.0139
  -7.500  -0.6936   0.02272   0.01536  -0.0263   1.0000   0.0144
  -7.250  -0.6756   0.02172   0.01425  -0.0248   1.0000   0.0152
  -7.000  -0.6578   0.02069   0.01311  -0.0232   1.0000   0.0156
  -6.750  -0.6404   0.01972   0.01204  -0.0216   1.0000   0.0159
  -6.500  -0.6233   0.01883   0.01106  -0.0198   1.0000   0.0162
  -6.250  -0.6063   0.01804   0.01017  -0.0180   1.0000   0.0166
  -6.000  -0.5894   0.01729   0.00935  -0.0162   1.0000   0.0169
  -5.750  -0.5649   0.01646   0.00845  -0.0161   0.9975   0.0178
  -5.500  -0.5315   0.01577   0.00766  -0.0176   0.9923   0.0189
  -5.250  -0.4974   0.01518   0.00696  -0.0192   0.9870   0.0207
  -5.000  -0.4640   0.01455   0.00631  -0.0207   0.9815   0.0255
  -4.750  -0.4308   0.01388   0.00568  -0.0220   0.9756   0.0390
  -4.500  -0.3977   0.01312   0.00513  -0.0236   0.9702   0.0834
  -4.250  -0.3670   0.01246   0.00474  -0.0246   0.9627   0.1397
  -4.000  -0.3341   0.01188   0.00441  -0.0261   0.9567   0.1999
  -3.750  -0.3047   0.01136   0.00415  -0.0268   0.9479   0.2664
  -3.500  -0.2738   0.01088   0.00394  -0.0277   0.9403   0.3331
  -3.250  -0.2439   0.01052   0.00375  -0.0282   0.9313   0.3866
  -3.000  -0.2146   0.01025   0.00356  -0.0284   0.9216   0.4274
  -2.750  -0.1844   0.01000   0.00340  -0.0288   0.9127   0.4669
  -2.500  -0.1570   0.00978   0.00327  -0.0286   0.9015   0.5056
  -2.250  -0.1299   0.00957   0.00316  -0.0283   0.8901   0.5427
  -2.000  -0.1029   0.00940   0.00305  -0.0278   0.8788   0.5790
  -1.750  -0.0762   0.00923   0.00296  -0.0273   0.8673   0.6139
  -1.500  -0.0503   0.00909   0.00289  -0.0266   0.8547   0.6481
  -1.250  -0.0246   0.00897   0.00283  -0.0258   0.8416   0.6814
  -1.000   0.0011   0.00888   0.00279  -0.0249   0.8282   0.7138
  -0.750   0.0267   0.00880   0.00276  -0.0241   0.8145   0.7446
  -0.500   0.0524   0.00874   0.00273  -0.0232   0.8003   0.7737
  -0.250   0.0783   0.00870   0.00272  -0.0223   0.7858   0.8020
   0.000   0.1045   0.00868   0.00271  -0.0215   0.7707   0.8287
   0.250   0.1314   0.00869   0.00271  -0.0209   0.7551   0.8541
   0.500   0.1598   0.00871   0.00272  -0.0206   0.7389   0.8773
   0.750   0.1894   0.00876   0.00273  -0.0205   0.7221   0.8987
   1.000   0.2216   0.00882   0.00275  -0.0211   0.7046   0.9169
   1.250   0.2553   0.00890   0.00277  -0.0221   0.6860   0.9332
   1.500   0.2899   0.00898   0.00279  -0.0233   0.6658   0.9478
   1.750   0.3246   0.00908   0.00283  -0.0246   0.6447   0.9608
   2.000   0.3594   0.00919   0.00287  -0.0260   0.6220   0.9730
   2.250   0.3957   0.00932   0.00291  -0.0277   0.5979   0.9828
   2.500   0.4329   0.00944   0.00297  -0.0298   0.5719   0.9914
   2.750   0.4697   0.00959   0.00303  -0.0318   0.5448   1.0000
   3.000   0.4914   0.00976   0.00312  -0.0306   0.5202   1.0000
   3.500   0.5353   0.01018   0.00338  -0.0284   0.4679   1.0000
   3.750   0.5574   0.01042   0.00353  -0.0273   0.4404   1.0000
   4.000   0.5795   0.01069   0.00372  -0.0263   0.4126   1.0000
   4.250   0.6015   0.01098   0.00394  -0.0252   0.3845   1.0000
   4.500   0.6235   0.01130   0.00417  -0.0242   0.3549   1.0000
   4.750   0.6453   0.01166   0.00443  -0.0231   0.3233   1.0000
   5.250   0.6886   0.01251   0.00506  -0.0211   0.2542   1.0000
   5.500   0.7096   0.01305   0.00542  -0.0201   0.2150   1.0000
   5.750   0.7306   0.01363   0.00583  -0.0191   0.1750   1.0000
   6.000   0.7515   0.01425   0.00629  -0.0181   0.1386   1.0000
   6.250   0.7722   0.01492   0.00679  -0.0172   0.1053   1.0000
   6.500   0.7930   0.01561   0.00733  -0.0163   0.0771   1.0000
   6.750   0.8138   0.01630   0.00792  -0.0153   0.0548   1.0000
   7.000   0.8338   0.01710   0.00863  -0.0142   0.0351   1.0000
   7.250   0.8537   0.01795   0.00947  -0.0131   0.0235   1.0000
   7.500   0.8738   0.01874   0.01029  -0.0120   0.0194   1.0000
   7.750   0.8936   0.01954   0.01114  -0.0109   0.0168   1.0000
   8.000   0.9131   0.02037   0.01207  -0.0097   0.0155   1.0000
   8.250   0.9320   0.02122   0.01305  -0.0085   0.0147   1.0000
   8.500   0.9501   0.02213   0.01408  -0.0073   0.0140   1.0000
   8.750   0.9668   0.02313   0.01519  -0.0059   0.0134   1.0000
   9.000   0.9820   0.02425   0.01641  -0.0043   0.0130   1.0000
   9.250   0.9952   0.02552   0.01776  -0.0026   0.0126   1.0000
   9.500   1.0069   0.02695   0.01928  -0.0008   0.0124   1.0000
   9.750   1.0199   0.02826   0.02072   0.0009   0.0122   1.0000
  10.000   1.0319   0.02965   0.02226   0.0027   0.0119   1.0000
  10.250   1.0424   0.03100   0.02378   0.0046   0.0116   1.0000
  10.500   1.0508   0.03253   0.02546   0.0067   0.0115   1.0000
  10.750   1.0578   0.03404   0.02715   0.0087   0.0109   1.0000
  11.000   1.0637   0.03575   0.02902   0.0105   0.0107   1.0000
  11.250   1.0681   0.03750   0.03093   0.0122   0.0104   1.0000
  11.500   1.0702   0.03959   0.03320   0.0137   0.0102   1.0000
  11.750   1.0708   0.04192   0.03573   0.0149   0.0101   1.0000
  12.000   1.0695   0.04448   0.03848   0.0158   0.0100   1.0000
  12.250   1.0663   0.04737   0.04156   0.0163   0.0099   1.0000
  12.500   1.0608   0.05061   0.04499   0.0162   0.0098   1.0000
  12.750   1.0530   0.05440   0.04899   0.0155   0.0098   1.0000
  13.000   1.0431   0.05874   0.05358   0.0142   0.0098   1.0000
  13.250   1.0322   0.06347   0.05851   0.0121   0.0098   1.0000
  13.500   1.0184   0.06908   0.06433   0.0092   0.0098   1.0000
  13.750   1.0030   0.07532   0.07076   0.0056   0.0097   1.0000
  14.000   0.9835   0.08294   0.07860   0.0009   0.0098   1.0000
  14.250   0.9614   0.09171   0.08757  -0.0048   0.0100   1.0000
  14.500   0.9351   0.10227   0.09834  -0.0117   0.0101   1.0000
  14.750   0.8933   0.11813   0.11443  -0.0215   0.0104   1.0000
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