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E211 (10.96%) (e211-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: E211 (10.96%) (e211-il)
Reynolds number: 200,000
Max Cl/Cd: 74.71 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e211-il-200000-n5.txt
Download as CSV file: xf-e211-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4754   0.09274   0.08908  -0.0389   1.0000   0.0169
 -10.000  -0.4817   0.08828   0.08467  -0.0401   1.0000   0.0167
  -9.750  -0.4900   0.08344   0.07987  -0.0415   1.0000   0.0165
  -9.500  -0.5022   0.07781   0.07430  -0.0435   1.0000   0.0163
  -9.250  -0.5214   0.07007   0.06662  -0.0470   1.0000   0.0161
  -9.000  -0.5555   0.06065   0.05719  -0.0526   1.0000   0.0158
  -8.750  -0.5841   0.05672   0.05323  -0.0530   1.0000   0.0157
  -8.500  -0.6056   0.05177   0.04810  -0.0538   1.0000   0.0156
  -8.250  -0.6198   0.04690   0.04297  -0.0536   1.0000   0.0154
  -8.000  -0.6207   0.04160   0.03727  -0.0549   0.9988   0.0153
  -7.750  -0.5997   0.03572   0.03074  -0.0594   0.9948   0.0152
  -7.500  -0.5755   0.03157   0.02602  -0.0619   0.9909   0.0152
  -7.250  -0.5474   0.02842   0.02234  -0.0640   0.9876   0.0153
  -7.000  -0.5162   0.02597   0.01945  -0.0660   0.9851   0.0155
  -6.750  -0.4875   0.02410   0.01724  -0.0670   0.9816   0.0158
  -6.500  -0.4574   0.02254   0.01541  -0.0681   0.9779   0.0162
  -6.250  -0.4250   0.02129   0.01394  -0.0695   0.9750   0.0166
  -6.000  -0.3918   0.01996   0.01247  -0.0713   0.9727   0.0177
  -5.750  -0.3649   0.01901   0.01148  -0.0716   0.9675   0.0187
  -5.500  -0.3334   0.01809   0.01047  -0.0727   0.9635   0.0193
  -5.250  -0.2992   0.01724   0.00953  -0.0744   0.9606   0.0200
  -5.000  -0.2710   0.01652   0.00870  -0.0747   0.9549   0.0209
  -4.750  -0.2390   0.01588   0.00795  -0.0758   0.9502   0.0219
  -4.500  -0.2038   0.01522   0.00722  -0.0776   0.9471   0.0239
  -4.250  -0.1768   0.01470   0.00666  -0.0776   0.9397   0.0274
  -4.000  -0.1429   0.01410   0.00609  -0.0790   0.9354   0.0403
  -3.750  -0.1133   0.01346   0.00561  -0.0797   0.9290   0.0774
  -3.500  -0.0814   0.01287   0.00522  -0.0809   0.9232   0.1272
  -3.250  -0.0488   0.01227   0.00486  -0.0822   0.9179   0.1918
  -3.000  -0.0194   0.01155   0.00455  -0.0831   0.9104   0.2944
  -2.750   0.0149   0.01074   0.00436  -0.0848   0.9061   0.4470
  -2.500   0.0436   0.01051   0.00428  -0.0849   0.8964   0.5161
  -2.250   0.0789   0.01033   0.00411  -0.0862   0.8898   0.5584
  -2.000   0.1128   0.01019   0.00397  -0.0873   0.8810   0.5846
  -1.750   0.1489   0.01007   0.00381  -0.0888   0.8725   0.6068
  -1.500   0.1874   0.00993   0.00365  -0.0908   0.8638   0.6260
  -1.250   0.2229   0.00983   0.00352  -0.0922   0.8523   0.6424
  -1.000   0.2595   0.00974   0.00339  -0.0938   0.8399   0.6574
  -0.750   0.2952   0.00968   0.00328  -0.0952   0.8264   0.6713
  -0.500   0.3293   0.00965   0.00320  -0.0963   0.8115   0.6844
  -0.250   0.3617   0.00964   0.00314  -0.0971   0.7958   0.6968
   0.000   0.3924   0.00967   0.00310  -0.0975   0.7797   0.7085
   0.250   0.4216   0.00970   0.00310  -0.0976   0.7636   0.7188
   0.500   0.4500   0.00976   0.00310  -0.0976   0.7478   0.7290
   0.750   0.4779   0.00983   0.00312  -0.0975   0.7322   0.7392
   1.000   0.5048   0.00990   0.00316  -0.0971   0.7172   0.7482
   1.250   0.5315   0.00998   0.00322  -0.0968   0.7026   0.7579
   1.500   0.5579   0.01008   0.00329  -0.0964   0.6883   0.7685
   1.750   0.5837   0.01016   0.00337  -0.0958   0.6743   0.7790
   2.000   0.6092   0.01025   0.00348  -0.0953   0.6604   0.7903
   2.250   0.6344   0.01035   0.00358  -0.0946   0.6460   0.8029
   2.500   0.6590   0.01045   0.00369  -0.0938   0.6311   0.8169
   2.750   0.6829   0.01056   0.00380  -0.0928   0.6157   0.8322
   3.000   0.7063   0.01066   0.00393  -0.0917   0.6002   0.8498
   3.250   0.7293   0.01076   0.00405  -0.0905   0.5849   0.8713
   3.500   0.7516   0.01084   0.00416  -0.0892   0.5691   0.8985
   3.750   0.7771   0.01092   0.00427  -0.0886   0.5514   0.9392
   4.000   0.8071   0.01106   0.00443  -0.0891   0.5317   1.0000
   4.250   0.8322   0.01130   0.00461  -0.0887   0.5122   1.0000
   4.500   0.8569   0.01155   0.00482  -0.0881   0.4915   1.0000
   4.750   0.8811   0.01181   0.00504  -0.0875   0.4689   1.0000
   5.000   0.9047   0.01211   0.00531  -0.0867   0.4445   1.0000
   5.250   0.9274   0.01245   0.00558  -0.0858   0.4168   1.0000
   5.500   0.9491   0.01285   0.00588  -0.0848   0.3832   1.0000
   5.750   0.9691   0.01336   0.00623  -0.0834   0.3421   1.0000
   6.000   0.9872   0.01402   0.00668  -0.0819   0.2916   1.0000
   6.250   1.0037   0.01485   0.00721  -0.0802   0.2355   1.0000
   6.500   1.0203   0.01573   0.00782  -0.0785   0.1854   1.0000
   6.750   1.0376   0.01658   0.00845  -0.0770   0.1453   1.0000
   7.000   1.0548   0.01744   0.00911  -0.0756   0.1098   1.0000
   7.250   1.0726   0.01824   0.00980  -0.0741   0.0838   1.0000
   7.500   1.0901   0.01904   0.01050  -0.0727   0.0622   1.0000
   7.750   1.1067   0.01989   0.01127  -0.0710   0.0440   1.0000
   8.000   1.1217   0.02085   0.01216  -0.0692   0.0284   1.0000
   8.250   1.1353   0.02183   0.01311  -0.0670   0.0200   1.0000
   8.500   1.1493   0.02272   0.01404  -0.0649   0.0165   1.0000
   8.750   1.1628   0.02364   0.01506  -0.0628   0.0147   1.0000
   9.000   1.1761   0.02456   0.01609  -0.0606   0.0137   1.0000
   9.250   1.1883   0.02556   0.01720  -0.0585   0.0130   1.0000
   9.500   1.1990   0.02664   0.01839  -0.0562   0.0124   1.0000
   9.750   1.2069   0.02793   0.01978  -0.0536   0.0119   1.0000
  10.000   1.2131   0.02935   0.02131  -0.0510   0.0116   1.0000
  10.250   1.2204   0.03073   0.02283  -0.0487   0.0113   1.0000
  10.500   1.2269   0.03223   0.02448  -0.0465   0.0111   1.0000
  10.750   1.2324   0.03387   0.02626  -0.0443   0.0109   1.0000
  11.000   1.2376   0.03562   0.02814  -0.0423   0.0107   1.0000
  11.250   1.2424   0.03751   0.03017  -0.0405   0.0105   1.0000
  11.500   1.2473   0.03943   0.03224  -0.0389   0.0102   1.0000
  11.750   1.2516   0.04151   0.03447  -0.0375   0.0099   1.0000
  12.000   1.2555   0.04362   0.03671  -0.0363   0.0095   1.0000
  12.250   1.2583   0.04599   0.03922  -0.0353   0.0093   1.0000
  12.500   1.2601   0.04848   0.04185  -0.0344   0.0091   1.0000
  12.750   1.2607   0.05122   0.04473  -0.0338   0.0089   1.0000
  13.250   1.2584   0.05753   0.05136  -0.0332   0.0086   1.0000
  13.500   1.2552   0.06114   0.05514  -0.0333   0.0085   1.0000
  13.750   1.2508   0.06502   0.05921  -0.0337   0.0084   1.0000
  14.000   1.2440   0.06938   0.06375  -0.0344   0.0083   1.0000
  14.250   1.2358   0.07412   0.06870  -0.0355   0.0083   1.0000
  14.500   1.2269   0.07911   0.07389  -0.0371   0.0083   1.0000
  14.750   1.2157   0.08469   0.07967  -0.0392   0.0082   1.0000
  15.250   1.1915   0.09697   0.09237  -0.0451   0.0082   1.0000
  15.500   1.1780   0.10382   0.09942  -0.0488   0.0082   1.0000
  16.000   1.1498   0.11897   0.11497  -0.0578   0.0083   1.0000
  16.250   1.1350   0.12739   0.12357  -0.0632   0.0083   1.0000
  16.500   1.1191   0.13660   0.13298  -0.0693   0.0084   1.0000
  16.750   1.0983   0.14799   0.14459  -0.0768   0.0085   1.0000
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