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E211 (10.96%) (e211-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: E211 (10.96%) (e211-il)
Reynolds number: 1,000,000
Max Cl/Cd: 118.08 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e211-il-1000000.txt
Download as CSV file: xf-e211-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5057   0.08394   0.08239  -0.0355   1.0000   0.0133
  -9.500  -0.5200   0.07804   0.07652  -0.0376   1.0000   0.0134
  -9.250  -0.5400   0.07115   0.06967  -0.0404   1.0000   0.0135
  -9.000  -0.6037   0.04447   0.04250  -0.0690   0.9933   0.0133
  -8.750  -0.5917   0.03972   0.03750  -0.0735   0.9891   0.0134
  -8.500  -0.5704   0.03624   0.03380  -0.0774   0.9867   0.0138
  -8.250  -0.5578   0.02535   0.02185  -0.0824   0.9844   0.0116
  -8.000  -0.5413   0.02274   0.01894  -0.0817   0.9796   0.0116
  -7.750  -0.5142   0.02033   0.01623  -0.0830   0.9774   0.0115
  -7.500  -0.4842   0.01846   0.01410  -0.0843   0.9759   0.0115
  -7.250  -0.4526   0.01699   0.01245  -0.0858   0.9747   0.0115
  -7.000  -0.4201   0.01566   0.01096  -0.0873   0.9738   0.0116
  -6.750  -0.3864   0.01470   0.00989  -0.0889   0.9730   0.0117
  -6.500  -0.3515   0.01402   0.00913  -0.0907   0.9724   0.0120
  -6.250  -0.3318   0.01326   0.00829  -0.0891   0.9668   0.0122
  -6.000  -0.3004   0.01254   0.00751  -0.0901   0.9646   0.0123
  -5.750  -0.2685   0.01132   0.00618  -0.0914   0.9629   0.0128
  -5.500  -0.2341   0.01054   0.00534  -0.0931   0.9616   0.0135
  -5.250  -0.1987   0.01002   0.00477  -0.0949   0.9606   0.0140
  -5.000  -0.1624   0.00958   0.00429  -0.0969   0.9598   0.0147
  -4.750  -0.1406   0.00921   0.00389  -0.0955   0.9532   0.0152
  -4.500  -0.1076   0.00884   0.00348  -0.0967   0.9505   0.0159
  -4.250  -0.0727   0.00849   0.00310  -0.0982   0.9485   0.0169
  -4.000  -0.0370   0.00808   0.00268  -0.0999   0.9468   0.0211
  -3.750  -0.0153   0.00760   0.00235  -0.0986   0.9383   0.0514
  -3.500   0.0191   0.00707   0.00205  -0.1002   0.9343   0.1080
  -3.250   0.0497   0.00669   0.00183  -0.1010   0.9264   0.1573
  -3.000   0.0873   0.00622   0.00159  -0.1033   0.9202   0.2289
  -2.750   0.1226   0.00573   0.00138  -0.1053   0.9094   0.3191
  -2.500   0.1583   0.00527   0.00120  -0.1073   0.8957   0.4202
  -2.250   0.1913   0.00505   0.00111  -0.1085   0.8776   0.4980
  -2.000   0.2207   0.00502   0.00107  -0.1087   0.8561   0.5318
  -1.750   0.2484   0.00506   0.00105  -0.1086   0.8338   0.5580
  -1.500   0.2751   0.00513   0.00104  -0.1082   0.8119   0.5738
  -1.250   0.3013   0.00520   0.00104  -0.1078   0.7905   0.5853
  -1.000   0.3276   0.00528   0.00104  -0.1074   0.7705   0.5956
  -0.750   0.3538   0.00536   0.00106  -0.1069   0.7512   0.6064
  -0.500   0.3801   0.00545   0.00108  -0.1065   0.7331   0.6163
  -0.250   0.4064   0.00553   0.00110  -0.1061   0.7161   0.6251
   0.000   0.4329   0.00562   0.00113  -0.1058   0.6999   0.6343
   0.250   0.4594   0.00568   0.00116  -0.1055   0.6842   0.6432
   0.500   0.4860   0.00577   0.00120  -0.1052   0.6687   0.6521
   0.750   0.5125   0.00585   0.00125  -0.1049   0.6528   0.6613
   1.000   0.5391   0.00593   0.00130  -0.1046   0.6370   0.6704
   1.500   0.5923   0.00610   0.00142  -0.1040   0.6078   0.6900
   1.750   0.6189   0.00618   0.00148  -0.1037   0.5936   0.7000
   2.000   0.6455   0.00628   0.00156  -0.1035   0.5788   0.7102
   2.250   0.6720   0.00636   0.00163  -0.1032   0.5640   0.7202
   2.500   0.6985   0.00646   0.00171  -0.1029   0.5490   0.7304
   2.750   0.7249   0.00656   0.00180  -0.1026   0.5333   0.7414
   3.000   0.7512   0.00666   0.00191  -0.1023   0.5173   0.7535
   3.250   0.7774   0.00677   0.00201  -0.1019   0.5010   0.7665
   3.500   0.8034   0.00688   0.00213  -0.1016   0.4845   0.7806
   3.750   0.8289   0.00702   0.00225  -0.1011   0.4656   0.7960
   4.250   0.8770   0.00746   0.00258  -0.0997   0.4042   0.8335
   4.500   0.8996   0.00777   0.00278  -0.0987   0.3635   0.8571
   4.750   0.9209   0.00806   0.00301  -0.0974   0.3247   0.8864
   5.000   0.9374   0.00833   0.00323  -0.0950   0.2857   0.9390
   5.250   0.9613   0.00889   0.00354  -0.0945   0.2298   1.0000
   5.500   0.9829   0.00949   0.00389  -0.0935   0.1811   1.0000
   5.750   1.0048   0.01005   0.00425  -0.0926   0.1421   1.0000
   6.000   1.0273   0.01054   0.00459  -0.0918   0.1125   1.0000
   6.250   1.0489   0.01111   0.00498  -0.0909   0.0826   1.0000
   6.500   1.0708   0.01163   0.00537  -0.0899   0.0592   1.0000
   6.750   1.0905   0.01234   0.00589  -0.0886   0.0309   1.0000
   7.000   1.1095   0.01309   0.00651  -0.0871   0.0127   1.0000
   7.250   1.1317   0.01356   0.00699  -0.0861   0.0105   1.0000
   7.500   1.1539   0.01399   0.00747  -0.0852   0.0097   1.0000
   7.750   1.1751   0.01451   0.00802  -0.0841   0.0088   1.0000
   8.000   1.1938   0.01522   0.00880  -0.0825   0.0080   1.0000
   8.250   1.2140   0.01576   0.00941  -0.0812   0.0078   1.0000
   8.500   1.2336   0.01633   0.01003  -0.0799   0.0076   1.0000
   8.750   1.2525   0.01692   0.01067  -0.0784   0.0074   1.0000
   9.000   1.2700   0.01756   0.01138  -0.0767   0.0073   1.0000
   9.250   1.2853   0.01822   0.01210  -0.0746   0.0071   1.0000
   9.500   1.2989   0.01893   0.01288  -0.0722   0.0069   1.0000
   9.750   1.3122   0.01965   0.01368  -0.0698   0.0068   1.0000
  10.000   1.3235   0.02049   0.01459  -0.0672   0.0067   1.0000
  10.250   1.3355   0.02129   0.01545  -0.0648   0.0065   1.0000
  10.500   1.3458   0.02221   0.01644  -0.0623   0.0063   1.0000
  10.750   1.3545   0.02324   0.01754  -0.0596   0.0062   1.0000
  11.000   1.3621   0.02437   0.01875  -0.0569   0.0061   1.0000
  11.250   1.3658   0.02582   0.02028  -0.0539   0.0059   1.0000
  11.500   1.3686   0.02742   0.02198  -0.0509   0.0058   1.0000
  11.750   1.3662   0.02963   0.02433  -0.0477   0.0057   1.0000
  12.000   1.3629   0.03227   0.02711  -0.0447   0.0056   1.0000
  12.250   1.3626   0.03485   0.02984  -0.0424   0.0056   1.0000
  12.500   1.3670   0.03664   0.03175  -0.0407   0.0055   1.0000
  12.750   1.3708   0.03845   0.03369  -0.0391   0.0055   1.0000
  13.000   1.3723   0.04068   0.03605  -0.0377   0.0055   1.0000
  13.250   1.3722   0.04322   0.03873  -0.0365   0.0054   1.0000
  13.500   1.3709   0.04594   0.04158  -0.0355   0.0054   1.0000
  13.750   1.3689   0.04884   0.04463  -0.0349   0.0054   1.0000
  14.000   1.3666   0.05186   0.04779  -0.0347   0.0053   1.0000
  14.250   1.3614   0.05545   0.05153  -0.0347   0.0053   1.0000
  14.500   1.3552   0.05934   0.05557  -0.0352   0.0052   1.0000
  14.750   1.3460   0.06389   0.06028  -0.0360   0.0052   1.0000
  15.000   1.3384   0.06838   0.06492  -0.0374   0.0052   1.0000
  15.250   1.3261   0.07390   0.07061  -0.0392   0.0052   1.0000
  15.500   1.3121   0.08000   0.07688  -0.0417   0.0052   1.0000
  15.750   1.2975   0.08652   0.08355  -0.0447   0.0052   1.0000
  16.000   1.2813   0.09371   0.09091  -0.0483   0.0053   1.0000
  16.250   1.2647   0.10139   0.09875  -0.0525   0.0053   1.0000
  16.500   1.2461   0.10983   0.10736  -0.0573   0.0053   1.0000
  16.750   1.2274   0.11875   0.11643  -0.0627   0.0053   1.0000
  17.000   1.2077   0.12835   0.12619  -0.0687   0.0054   1.0000
  17.250   1.1849   0.13912   0.13710  -0.0755   0.0054   1.0000
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