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E205 (10.48%) (e205-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: E205 (10.48%) (e205-il)
Reynolds number: 100,000
Max Cl/Cd: 54.9 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e205-il-100000-n5.txt
Download as CSV file: xf-e205-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4072   0.09010   0.08523  -0.0297   1.0000   0.0327
  -8.750  -0.4089   0.08598   0.08118  -0.0318   1.0000   0.0329
  -8.500  -0.4122   0.08176   0.07703  -0.0340   1.0000   0.0328
  -8.250  -0.4173   0.07760   0.07295  -0.0362   1.0000   0.0326
  -8.000  -0.4263   0.07331   0.06875  -0.0385   1.0000   0.0322
  -7.750  -0.4332   0.06837   0.06385  -0.0415   1.0000   0.0313
  -7.500  -0.4400   0.06301   0.05848  -0.0440   1.0000   0.0311
  -7.250  -0.4471   0.05762   0.05300  -0.0453   1.0000   0.0305
  -7.000  -0.4538   0.05227   0.04749  -0.0454   1.0000   0.0297
  -6.750  -0.4598   0.04712   0.04207  -0.0444   1.0000   0.0290
  -6.500  -0.4557   0.04114   0.03553  -0.0447   0.9949   0.0282
  -6.250  -0.4285   0.03576   0.02943  -0.0478   0.9819   0.0278
  -6.000  -0.3988   0.03206   0.02517  -0.0499   0.9690   0.0279
  -5.750  -0.3675   0.02915   0.02177  -0.0516   0.9561   0.0282
  -5.500  -0.3363   0.02681   0.01900  -0.0528   0.9417   0.0287
  -5.250  -0.3044   0.02484   0.01668  -0.0539   0.9267   0.0295
  -5.000  -0.2716   0.02328   0.01484  -0.0549   0.9117   0.0310
  -4.750  -0.2387   0.02204   0.01332  -0.0558   0.8960   0.0337
  -4.500  -0.2066   0.02084   0.01185  -0.0564   0.8799   0.0354
  -4.250  -0.1775   0.01951   0.01039  -0.0565   0.8633   0.0370
  -4.000  -0.1495   0.01861   0.00938  -0.0564   0.8465   0.0393
  -3.750  -0.1224   0.01786   0.00847  -0.0559   0.8300   0.0429
  -3.500  -0.0963   0.01717   0.00761  -0.0553   0.8144   0.0485
  -3.250  -0.0709   0.01648   0.00690  -0.0546   0.7993   0.0641
  -3.000  -0.0460   0.01579   0.00635  -0.0540   0.7851   0.1108
  -2.750  -0.0214   0.01517   0.00602  -0.0535   0.7717   0.1886
  -2.500   0.0025   0.01453   0.00579  -0.0530   0.7588   0.2978
  -2.250   0.0265   0.01396   0.00559  -0.0522   0.7469   0.4133
  -2.000   0.0502   0.01340   0.00542  -0.0512   0.7359   0.5472
  -1.500   0.1365   0.01258   0.00530  -0.0550   0.7151   0.8917
  -1.250   0.1895   0.01266   0.00512  -0.0596   0.7046   0.9611
  -1.000   0.2433   0.01267   0.00485  -0.0649   0.6949   0.9963
  -0.750   0.2715   0.01273   0.00471  -0.0651   0.6853   1.0000
  -0.500   0.2951   0.01282   0.00463  -0.0644   0.6760   1.0000
  -0.250   0.3189   0.01293   0.00455  -0.0636   0.6682   1.0000
   0.000   0.3428   0.01304   0.00455  -0.0629   0.6591   1.0000
   0.250   0.3669   0.01317   0.00454  -0.0621   0.6514   1.0000
   0.500   0.3910   0.01331   0.00456  -0.0615   0.6432   1.0000
   0.750   0.4152   0.01345   0.00461  -0.0608   0.6358   1.0000
   1.000   0.4395   0.01361   0.00467  -0.0601   0.6282   1.0000
   1.250   0.4639   0.01377   0.00476  -0.0594   0.6211   1.0000
   1.500   0.4884   0.01394   0.00486  -0.0588   0.6139   1.0000
   1.750   0.5128   0.01413   0.00499  -0.0581   0.6069   1.0000
   2.000   0.5373   0.01431   0.00514  -0.0575   0.5999   1.0000
   2.250   0.5619   0.01451   0.00529  -0.0568   0.5932   1.0000
   2.500   0.5863   0.01471   0.00548  -0.0562   0.5861   1.0000
   2.750   0.6109   0.01492   0.00567  -0.0555   0.5798   1.0000
   3.000   0.6352   0.01513   0.00591  -0.0549   0.5725   1.0000
   3.250   0.6600   0.01535   0.00610  -0.0543   0.5664   1.0000
   3.500   0.6841   0.01559   0.00641  -0.0536   0.5587   1.0000
   3.750   0.7091   0.01580   0.00660  -0.0530   0.5527   1.0000
   4.000   0.7329   0.01605   0.00693  -0.0523   0.5446   1.0000
   4.250   0.7577   0.01627   0.00715  -0.0517   0.5380   1.0000
   4.500   0.7815   0.01651   0.00748  -0.0509   0.5293   1.0000
   4.750   0.8057   0.01673   0.00778  -0.0502   0.5211   1.0000
   5.000   0.8298   0.01694   0.00804  -0.0495   0.5123   1.0000
   5.250   0.8531   0.01716   0.00837  -0.0486   0.5023   1.0000
   5.500   0.8769   0.01736   0.00862  -0.0478   0.4926   1.0000
   5.750   0.9007   0.01753   0.00888  -0.0470   0.4824   1.0000
   6.000   0.9234   0.01774   0.00922  -0.0460   0.4702   1.0000
   6.250   0.9461   0.01795   0.00954  -0.0450   0.4576   1.0000
   6.500   0.9685   0.01816   0.00985  -0.0440   0.4440   1.0000
   6.750   0.9905   0.01836   0.01016  -0.0429   0.4290   1.0000
   7.000   1.0121   0.01858   0.01050  -0.0418   0.4124   1.0000
   7.250   1.0328   0.01886   0.01089  -0.0405   0.3929   1.0000
   7.500   1.0525   0.01917   0.01126  -0.0391   0.3708   1.0000
   7.750   1.0711   0.01957   0.01171  -0.0376   0.3439   1.0000
   8.000   1.0878   0.02009   0.01222  -0.0359   0.3121   1.0000
   8.250   1.1020   0.02081   0.01285  -0.0339   0.2739   1.0000
   8.500   1.1135   0.02176   0.01370  -0.0317   0.2358   1.0000
   8.750   1.1221   0.02293   0.01471  -0.0293   0.2007   1.0000
   9.000   1.1291   0.02421   0.01586  -0.0268   0.1684   1.0000
   9.250   1.1335   0.02561   0.01711  -0.0241   0.1388   1.0000
   9.500   1.1357   0.02705   0.01841  -0.0212   0.1129   1.0000
   9.750   1.1353   0.02854   0.01977  -0.0181   0.0914   1.0000
  10.000   1.1357   0.03009   0.02125  -0.0155   0.0741   1.0000
  10.250   1.1355   0.03183   0.02297  -0.0132   0.0603   1.0000
  10.500   1.1349   0.03376   0.02490  -0.0112   0.0493   1.0000
  10.750   1.1332   0.03597   0.02713  -0.0097   0.0401   1.0000
  11.000   1.1306   0.03843   0.02966  -0.0084   0.0334   1.0000
  11.250   1.1277   0.04108   0.03237  -0.0075   0.0291   1.0000
  11.500   1.1228   0.04409   0.03544  -0.0068   0.0265   1.0000
  11.750   1.1214   0.04687   0.03839  -0.0063   0.0246   1.0000
  12.000   1.1194   0.04981   0.04147  -0.0061   0.0229   1.0000
  12.250   1.1176   0.05281   0.04459  -0.0060   0.0219   1.0000
  12.500   1.1153   0.05593   0.04782  -0.0060   0.0211   1.0000
  12.750   1.1112   0.05934   0.05133  -0.0062   0.0203   1.0000
  13.000   1.1088   0.06260   0.05467  -0.0062   0.0197   1.0000
  13.250   1.1096   0.06559   0.05785  -0.0062   0.0190   1.0000
  13.500   1.1099   0.06871   0.06115  -0.0064   0.0182   1.0000
  13.750   1.1094   0.07203   0.06463  -0.0068   0.0175   1.0000
  14.000   1.1085   0.07549   0.06824  -0.0074   0.0170   1.0000
  14.250   1.1054   0.07937   0.07227  -0.0085   0.0162   1.0000
  14.500   1.1018   0.08344   0.07646  -0.0098   0.0157   1.0000
  14.750   1.0981   0.08763   0.08079  -0.0112   0.0154   1.0000
  15.000   1.0939   0.09203   0.08536  -0.0127   0.0151   1.0000
  15.250   1.0890   0.09665   0.09014  -0.0144   0.0149   1.0000
  15.500   1.0825   0.10167   0.09529  -0.0163   0.0147   1.0000
  15.750   1.0755   0.10702   0.10080  -0.0186   0.0145   1.0000
  16.000   1.0666   0.11295   0.10690  -0.0214   0.0145   1.0000
  16.250   1.0566   0.11936   0.11350  -0.0248   0.0145   1.0000
  16.500   1.0439   0.12667   0.12100  -0.0288   0.0145   1.0000
  16.750   1.0316   0.13417   0.12867  -0.0332   0.0145   1.0000
  17.000   1.0165   0.14285   0.13755  -0.0383   0.0146   1.0000
  17.250   0.9858   0.15752   0.15246  -0.0473   0.0151   1.0000
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