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E211 (10.96%) (e211-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: E211 (10.96%) (e211-il)
Reynolds number: 500,000
Max Cl/Cd: 106.06 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e211-il-500000.txt
Download as CSV file: xf-e211-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4713   0.08633   0.08415  -0.0359   1.0000   0.0250
  -9.000  -0.4787   0.08231   0.08016  -0.0368   1.0000   0.0256
  -8.750  -0.4909   0.07767   0.07557  -0.0381   1.0000   0.0256
  -8.500  -0.5087   0.07271   0.07066  -0.0395   1.0000   0.0260
  -8.250  -0.5502   0.06533   0.06333  -0.0432   1.0000   0.0251
  -8.000  -0.5734   0.05892   0.05681  -0.0468   0.9998   0.0251
  -7.750  -0.4909   0.03660   0.03388  -0.0642   0.9880   0.0293
  -7.500  -0.4906   0.02550   0.02249  -0.0697   0.9850   0.0309
  -7.250  -0.4689   0.02312   0.02006  -0.0712   0.9813   0.0319
  -7.000  -0.4955   0.02659   0.02216  -0.0713   0.9837   0.0208
  -6.750  -0.4722   0.02137   0.01621  -0.0717   0.9798   0.0183
  -6.500  -0.4403   0.01973   0.01435  -0.0731   0.9772   0.0186
  -6.250  -0.4072   0.01776   0.01211  -0.0744   0.9754   0.0180
  -6.000  -0.3724   0.01645   0.01063  -0.0761   0.9739   0.0179
  -5.750  -0.3363   0.01538   0.00948  -0.0781   0.9726   0.0185
  -5.500  -0.3094   0.01453   0.00857  -0.0781   0.9676   0.0189
  -5.250  -0.2761   0.01376   0.00774  -0.0794   0.9645   0.0195
  -5.000  -0.2403   0.01307   0.00698  -0.0813   0.9622   0.0203
  -4.750  -0.2030   0.01247   0.00631  -0.0834   0.9605   0.0213
  -4.500  -0.1706   0.01195   0.00574  -0.0844   0.9568   0.0226
  -4.250  -0.1399   0.01133   0.00508  -0.0851   0.9517   0.0256
  -4.000  -0.1035   0.01083   0.00456  -0.0869   0.9491   0.0316
  -3.750  -0.0661   0.01000   0.00405  -0.0893   0.9472   0.0978
  -3.500  -0.0373   0.00945   0.00372  -0.0897   0.9411   0.1589
  -3.250  -0.0035   0.00880   0.00340  -0.0913   0.9370   0.2443
  -3.000   0.0326   0.00802   0.00308  -0.0935   0.9344   0.3681
  -2.750   0.0623   0.00751   0.00287  -0.0940   0.9282   0.4649
  -2.500   0.0954   0.00719   0.00273  -0.0950   0.9226   0.5337
  -2.250   0.1347   0.00698   0.00256  -0.0973   0.9191   0.5706
  -2.000   0.1659   0.00684   0.00243  -0.0978   0.9091   0.5938
  -1.750   0.2039   0.00670   0.00229  -0.0998   0.9011   0.6127
  -1.500   0.2435   0.00657   0.00214  -0.1022   0.8916   0.6269
  -1.250   0.2799   0.00650   0.00202  -0.1038   0.8778   0.6399
  -1.000   0.3145   0.00647   0.00193  -0.1051   0.8613   0.6521
  -0.750   0.3455   0.00649   0.00188  -0.1056   0.8421   0.6632
  -0.500   0.3749   0.00653   0.00185  -0.1058   0.8222   0.6730
  -0.250   0.4031   0.00661   0.00184  -0.1057   0.8027   0.6831
   0.000   0.4301   0.00669   0.00186  -0.1054   0.7831   0.6933
   0.250   0.4565   0.00677   0.00189  -0.1049   0.7644   0.7028
   0.500   0.4829   0.00687   0.00192  -0.1045   0.7468   0.7128
   0.750   0.5091   0.00697   0.00196  -0.1041   0.7300   0.7232
   1.000   0.5350   0.00705   0.00202  -0.1036   0.7136   0.7329
   1.250   0.5610   0.00714   0.00208  -0.1031   0.6973   0.7431
   1.500   0.5869   0.00724   0.00214  -0.1026   0.6809   0.7539
   1.750   0.6125   0.00732   0.00222  -0.1021   0.6649   0.7638
   2.000   0.6381   0.00741   0.00230  -0.1016   0.6494   0.7747
   2.250   0.6638   0.00750   0.00239  -0.1011   0.6345   0.7866
   2.500   0.6892   0.00760   0.00248  -0.1005   0.6194   0.7997
   2.750   0.7143   0.00769   0.00258  -0.0998   0.6041   0.8140
   3.000   0.7389   0.00777   0.00269  -0.0991   0.5888   0.8297
   3.250   0.7629   0.00785   0.00281  -0.0982   0.5733   0.8481
   3.500   0.7861   0.00793   0.00292  -0.0971   0.5578   0.8706
   3.750   0.8073   0.00798   0.00303  -0.0955   0.5423   0.8998
   4.000   0.8278   0.00798   0.00311  -0.0937   0.5266   0.9505
   4.500   0.8845   0.00834   0.00337  -0.0942   0.4867   1.0000
   4.750   0.9090   0.00860   0.00354  -0.0937   0.4599   1.0000
   5.000   0.9328   0.00890   0.00374  -0.0930   0.4286   1.0000
   5.250   0.9552   0.00931   0.00397  -0.0921   0.3879   1.0000
   5.500   0.9768   0.00980   0.00425  -0.0910   0.3408   1.0000
   5.750   0.9970   0.01044   0.00462  -0.0898   0.2855   1.0000
   6.250   1.0366   0.01185   0.00552  -0.0874   0.1853   1.0000
   6.500   1.0562   0.01256   0.00601  -0.0862   0.1433   1.0000
   6.750   1.0755   0.01329   0.00652  -0.0849   0.1069   1.0000
   7.000   1.0953   0.01395   0.00705  -0.0837   0.0794   1.0000
   7.250   1.1134   0.01475   0.00766  -0.0822   0.0484   1.0000
   7.500   1.1275   0.01588   0.00855  -0.0800   0.0204   1.0000
   7.750   1.1467   0.01655   0.00924  -0.0785   0.0165   1.0000
   8.000   1.1643   0.01734   0.01009  -0.0767   0.0147   1.0000
   8.250   1.1826   0.01800   0.01085  -0.0752   0.0138   1.0000
   8.500   1.1992   0.01872   0.01165  -0.0733   0.0131   1.0000
   8.750   1.2139   0.01946   0.01245  -0.0711   0.0124   1.0000
   9.000   1.2264   0.02032   0.01336  -0.0687   0.0119   1.0000
   9.250   1.2345   0.02146   0.01458  -0.0655   0.0113   1.0000
   9.500   1.2385   0.02291   0.01614  -0.0619   0.0110   1.0000
   9.750   1.2497   0.02390   0.01722  -0.0595   0.0108   1.0000
  10.000   1.2591   0.02505   0.01847  -0.0570   0.0107   1.0000
  10.250   1.2689   0.02620   0.01973  -0.0546   0.0105   1.0000
  10.500   1.2777   0.02750   0.02114  -0.0522   0.0104   1.0000
  10.750   1.2859   0.02893   0.02267  -0.0499   0.0102   1.0000
  11.000   1.2938   0.03045   0.02431  -0.0477   0.0101   1.0000
  11.250   1.3013   0.03211   0.02610  -0.0456   0.0099   1.0000
  11.500   1.3084   0.03390   0.02802  -0.0436   0.0098   1.0000
  11.750   1.3149   0.03580   0.03006  -0.0418   0.0097   1.0000
  12.000   1.3205   0.03788   0.03229  -0.0400   0.0096   1.0000
  12.250   1.3246   0.04021   0.03479  -0.0383   0.0096   1.0000
  12.500   1.3268   0.04282   0.03761  -0.0366   0.0095   1.0000
  12.750   1.3265   0.04570   0.04069  -0.0351   0.0095   1.0000
  13.000   1.3229   0.04900   0.04422  -0.0338   0.0096   1.0000
  13.250   1.3162   0.05275   0.04821  -0.0328   0.0097   1.0000
  13.500   1.3060   0.05699   0.05269  -0.0322   0.0098   1.0000
  13.750   1.2927   0.06178   0.05773  -0.0323   0.0099   1.0000
  14.000   1.2775   0.06702   0.06320  -0.0330   0.0100   1.0000
  14.250   1.2606   0.07275   0.06915  -0.0344   0.0102   1.0000
  14.500   1.2415   0.07918   0.07579  -0.0367   0.0103   1.0000
  14.750   1.2220   0.08609   0.08290  -0.0397   0.0104   1.0000
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