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E205 (10.48%) (e205-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: E205 (10.48%) (e205-il)
Reynolds number: 1,000,000
Max Cl/Cd: 128.32 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e205-il-1000000.txt
Download as CSV file: xf-e205-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E205  (10.48%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3308   0.09256   0.09105  -0.0255   1.0000   0.0136
 -10.000  -0.3340   0.08683   0.08533  -0.0278   1.0000   0.0146
  -9.750  -0.4208   0.09294   0.09135  -0.0253   1.0000   0.0125
  -9.500  -0.4198   0.08916   0.08758  -0.0270   1.0000   0.0131
  -9.250  -0.4220   0.08437   0.08281  -0.0294   1.0000   0.0140
  -7.750  -0.4689   0.04290   0.04097  -0.0554   0.9911   0.0149
  -7.500  -0.4765   0.02980   0.02702  -0.0607   0.9764   0.0154
  -7.250  -0.4541   0.02648   0.02345  -0.0621   0.9615   0.0159
  -7.000  -0.4261   0.02536   0.02226  -0.0632   0.9367   0.0164
  -6.750  -0.4205   0.01880   0.01478  -0.0598   0.8968   0.0132
  -6.500  -0.4021   0.01698   0.01255  -0.0581   0.8630   0.0132
  -6.250  -0.3810   0.01575   0.01100  -0.0568   0.8341   0.0134
  -6.000  -0.3584   0.01476   0.00974  -0.0557   0.8087   0.0136
  -5.750  -0.3349   0.01386   0.00861  -0.0548   0.7855   0.0137
  -5.500  -0.3109   0.01310   0.00766  -0.0541   0.7652   0.0138
  -5.250  -0.2863   0.01239   0.00678  -0.0533   0.7465   0.0140
  -5.000  -0.2614   0.01179   0.00604  -0.0527   0.7292   0.0142
  -4.750  -0.2359   0.01136   0.00548  -0.0522   0.7134   0.0145
  -4.500  -0.2097   0.01107   0.00509  -0.0517   0.6992   0.0148
  -4.250  -0.1851   0.01040   0.00429  -0.0510   0.6861   0.0152
  -4.000  -0.1606   0.00973   0.00349  -0.0503   0.6742   0.0159
  -3.750  -0.1347   0.00939   0.00305  -0.0499   0.6629   0.0166
  -3.500  -0.1081   0.00914   0.00273  -0.0495   0.6522   0.0172
  -3.250  -0.0813   0.00893   0.00245  -0.0493   0.6424   0.0180
  -3.000  -0.0544   0.00876   0.00219  -0.0490   0.6333   0.0188
  -2.750  -0.0271   0.00860   0.00198  -0.0487   0.6246   0.0199
  -2.500  -0.0001   0.00841   0.00175  -0.0485   0.6165   0.0238
  -2.250   0.0263   0.00811   0.00156  -0.0481   0.6085   0.0571
  -2.000   0.0525   0.00782   0.00143  -0.0479   0.6015   0.1087
  -1.750   0.0791   0.00758   0.00134  -0.0477   0.5941   0.1596
  -1.500   0.1056   0.00737   0.00127  -0.0475   0.5874   0.2138
  -1.250   0.1320   0.00711   0.00121  -0.0472   0.5808   0.2824
  -1.000   0.1578   0.00685   0.00117  -0.0469   0.5746   0.3668
  -0.750   0.1832   0.00650   0.00114  -0.0466   0.5683   0.4766
  -0.500   0.2076   0.00616   0.00113  -0.0460   0.5622   0.5939
  -0.250   0.2306   0.00576   0.00114  -0.0449   0.5568   0.7248
   0.000   0.2509   0.00533   0.00118  -0.0430   0.5511   0.8737
   0.250   0.2920   0.00536   0.00132  -0.0454   0.5448   0.9593
   0.500   0.3285   0.00544   0.00136  -0.0471   0.5390   0.9748
   0.750   0.3660   0.00555   0.00140  -0.0492   0.5327   0.9839
   1.000   0.4122   0.00561   0.00142  -0.0532   0.5267   0.9882
   1.250   0.4523   0.00568   0.00143  -0.0558   0.5204   0.9929
   1.500   0.4940   0.00573   0.00144  -0.0589   0.5143   0.9963
   1.750   0.5361   0.00576   0.00143  -0.0620   0.5075   0.9996
   2.000   0.5640   0.00582   0.00145  -0.0621   0.5014   1.0000
   2.250   0.5895   0.00585   0.00147  -0.0616   0.4949   1.0000
   2.750   0.6400   0.00598   0.00155  -0.0605   0.4809   1.0000
   3.250   0.6906   0.00612   0.00165  -0.0594   0.4664   1.0000
   3.500   0.7155   0.00622   0.00172  -0.0589   0.4587   1.0000
   3.750   0.7410   0.00628   0.00179  -0.0584   0.4511   1.0000
   4.000   0.7660   0.00639   0.00187  -0.0578   0.4430   1.0000
   4.250   0.7912   0.00648   0.00196  -0.0573   0.4343   1.0000
   4.500   0.8162   0.00658   0.00205  -0.0567   0.4251   1.0000
   4.750   0.8409   0.00672   0.00215  -0.0561   0.4154   1.0000
   5.000   0.8660   0.00682   0.00226  -0.0555   0.4050   1.0000
   5.250   0.8907   0.00696   0.00239  -0.0549   0.3939   1.0000
   5.500   0.9149   0.00713   0.00252  -0.0543   0.3784   1.0000
   5.750   0.9382   0.00737   0.00269  -0.0534   0.3559   1.0000
   6.000   0.9606   0.00769   0.00288  -0.0525   0.3260   1.0000
   6.250   0.9824   0.00807   0.00314  -0.0515   0.2933   1.0000
   6.500   1.0028   0.00855   0.00345  -0.0503   0.2556   1.0000
   6.750   1.0211   0.00921   0.00386  -0.0488   0.2080   1.0000
   7.000   1.0391   0.00988   0.00431  -0.0472   0.1653   1.0000
   7.250   1.0580   0.01046   0.00473  -0.0458   0.1340   1.0000
   7.500   1.0766   0.01105   0.00517  -0.0444   0.1045   1.0000
   7.750   1.0954   0.01163   0.00562  -0.0430   0.0803   1.0000
   8.000   1.1138   0.01224   0.00611  -0.0415   0.0589   1.0000
   8.250   1.1319   0.01287   0.00663  -0.0400   0.0399   1.0000
   8.500   1.1455   0.01383   0.00741  -0.0379   0.0151   1.0000
   8.750   1.1630   0.01449   0.00804  -0.0363   0.0097   1.0000
   9.000   1.1815   0.01505   0.00865  -0.0349   0.0083   1.0000
   9.250   1.2002   0.01556   0.00922  -0.0335   0.0078   1.0000
   9.500   1.2180   0.01612   0.00983  -0.0321   0.0073   1.0000
   9.750   1.2348   0.01670   0.01046  -0.0305   0.0069   1.0000
  10.000   1.2445   0.01770   0.01156  -0.0278   0.0061   1.0000
  10.250   1.2543   0.01848   0.01242  -0.0252   0.0060   1.0000
  10.500   1.2635   0.01916   0.01316  -0.0224   0.0059   1.0000
  10.750   1.2716   0.01993   0.01401  -0.0196   0.0058   1.0000
  11.000   1.2780   0.02087   0.01502  -0.0169   0.0057   1.0000
  11.250   1.2869   0.02173   0.01595  -0.0148   0.0056   1.0000
  11.500   1.2911   0.02295   0.01726  -0.0124   0.0055   1.0000
  11.750   1.2947   0.02435   0.01875  -0.0103   0.0055   1.0000
  12.000   1.3001   0.02575   0.02023  -0.0088   0.0053   1.0000
  12.250   1.3011   0.02763   0.02222  -0.0072   0.0052   1.0000
  12.500   1.3032   0.02959   0.02426  -0.0061   0.0052   1.0000
  12.750   1.3053   0.03166   0.02643  -0.0053   0.0051   1.0000
  13.000   1.3099   0.03361   0.02845  -0.0047   0.0049   1.0000
  13.250   1.3103   0.03605   0.03099  -0.0042   0.0049   1.0000
  13.500   1.3122   0.03843   0.03344  -0.0040   0.0048   1.0000
  13.750   1.3057   0.04175   0.03690  -0.0037   0.0049   1.0000
  14.000   1.3085   0.04416   0.03937  -0.0038   0.0047   1.0000
  14.250   1.3058   0.04722   0.04252  -0.0038   0.0047   1.0000
  14.500   1.3029   0.05036   0.04576  -0.0041   0.0046   1.0000
  14.750   1.2988   0.05374   0.04924  -0.0043   0.0047   1.0000
  15.000   1.2932   0.05739   0.05296  -0.0050   0.0044   1.0000
  15.250   1.2877   0.06117   0.05684  -0.0057   0.0044   1.0000
  15.500   1.2775   0.06561   0.06138  -0.0065   0.0043   1.0000
  15.750   1.2796   0.06874   0.06462  -0.0075   0.0044   1.0000
  16.000   1.2666   0.07378   0.06978  -0.0087   0.0042   1.0000
  16.250   1.2623   0.07793   0.07403  -0.0100   0.0043   1.0000
  16.500   1.2601   0.08194   0.07814  -0.0116   0.0043   1.0000
  16.750   1.2433   0.08800   0.08436  -0.0133   0.0042   1.0000
  17.000   1.2367   0.09293   0.08940  -0.0154   0.0042   1.0000
  17.250   1.2207   0.09942   0.09606  -0.0179   0.0041   1.0000
  17.500   1.2031   0.10660   0.10342  -0.0210   0.0041   1.0000
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