Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

E209 (13.72%) (e209-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E209 (13.72%) (e209-il)
Reynolds number: 100,000
Max Cl/Cd: 50.82 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e209-il-100000.txt
Download as CSV file: xf-e209-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E209  (13.72%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3760   0.10006   0.09552  -0.0379   1.0000   0.1517
 -10.250  -0.5544   0.07258   0.06768  -0.0577   1.0000   0.0665
 -10.000  -0.5733   0.06735   0.06243  -0.0598   1.0000   0.0651
  -9.750  -0.5995   0.06305   0.05809  -0.0604   1.0000   0.0639
  -9.500  -0.6293   0.05949   0.05444  -0.0582   1.0000   0.0626
  -9.250  -0.6583   0.05502   0.04973  -0.0557   1.0000   0.0606
  -9.000  -0.6990   0.05053   0.04440  -0.0508   1.0000   0.0569
  -8.750  -0.6985   0.04793   0.04149  -0.0481   1.0000   0.0563
  -8.500  -0.6996   0.04482   0.03807  -0.0453   1.0000   0.0565
  -8.250  -0.6982   0.04093   0.03394  -0.0429   1.0000   0.0572
  -8.000  -0.6901   0.03831   0.03125  -0.0410   1.0000   0.0591
  -7.750  -0.6804   0.03621   0.02900  -0.0388   1.0000   0.0605
  -7.500  -0.6712   0.03396   0.02646  -0.0363   1.0000   0.0616
  -7.250  -0.6604   0.03190   0.02413  -0.0338   1.0000   0.0630
  -7.000  -0.6486   0.03028   0.02221  -0.0315   1.0000   0.0656
  -6.750  -0.6369   0.02900   0.02057  -0.0290   1.0000   0.0688
  -6.500  -0.6231   0.02714   0.01880  -0.0273   1.0000   0.0722
  -6.250  -0.6098   0.02603   0.01762  -0.0253   1.0000   0.0763
  -6.000  -0.5965   0.02512   0.01652  -0.0233   1.0000   0.0819
  -5.750  -0.5719   0.02389   0.01543  -0.0237   0.9969   0.0912
  -5.500  -0.5289   0.02228   0.01394  -0.0272   0.9877   0.1122
  -5.250  -0.4891   0.02062   0.01263  -0.0304   0.9774   0.1596
  -5.000  -0.4517   0.01894   0.01157  -0.0336   0.9664   0.2545
  -4.750  -0.4137   0.01805   0.01145  -0.0363   0.9554   0.3930
  -4.500  -0.3739   0.01820   0.01167  -0.0384   0.9432   0.4726
  -4.250  -0.3363   0.01834   0.01177  -0.0399   0.9308   0.5175
  -4.000  -0.2983   0.01844   0.01179  -0.0413   0.9194   0.5533
  -3.750  -0.2508   0.01844   0.01171  -0.0443   0.9129   0.5867
  -3.500  -0.2162   0.01840   0.01167  -0.0449   0.9009   0.6103
  -3.250  -0.1809   0.01829   0.01144  -0.0459   0.8900   0.6339
  -3.000  -0.1382   0.01809   0.01121  -0.0477   0.8830   0.6543
  -2.750  -0.1078   0.01798   0.01105  -0.0476   0.8707   0.6723
  -2.500  -0.0768   0.01785   0.01086  -0.0477   0.8593   0.6896
  -2.250  -0.0435   0.01767   0.01060  -0.0481   0.8496   0.7063
  -2.000  -0.0128   0.01752   0.01038  -0.0481   0.8391   0.7220
  -1.750   0.0135   0.01745   0.01026  -0.0474   0.8272   0.7367
  -1.500   0.0411   0.01736   0.01012  -0.0469   0.8166   0.7515
  -1.250   0.0709   0.01723   0.00991  -0.0467   0.8075   0.7662
  -1.000   0.0947   0.01722   0.00988  -0.0457   0.7959   0.7808
  -0.750   0.1202   0.01720   0.00983  -0.0449   0.7859   0.7960
  -0.500   0.1485   0.01713   0.00970  -0.0445   0.7773   0.8117
  -0.250   0.1718   0.01719   0.00976  -0.0435   0.7666   0.8285
   0.000   0.1991   0.01720   0.00974  -0.0430   0.7580   0.8463
   0.250   0.2266   0.01724   0.00976  -0.0426   0.7488   0.8654
   0.500   0.2575   0.01737   0.00989  -0.0429   0.7395   0.8842
   0.750   0.2968   0.01742   0.00989  -0.0446   0.7318   0.9036
   1.000   0.3353   0.01763   0.01011  -0.0468   0.7220   0.9251
   1.250   0.3869   0.01771   0.01010  -0.0512   0.7145   0.9424
   1.500   0.4416   0.01788   0.01027  -0.0569   0.7044   0.9590
   1.750   0.4989   0.01796   0.01032  -0.0632   0.6955   0.9757
   2.000   0.5574   0.01793   0.01026  -0.0698   0.6868   0.9933
   2.250   0.5826   0.01809   0.01043  -0.0710   0.6778   1.0000
   2.500   0.5947   0.01823   0.01050  -0.0688   0.6709   1.0000
   2.750   0.6047   0.01866   0.01094  -0.0665   0.6623   1.0000
   3.000   0.6248   0.01888   0.01111  -0.0652   0.6556   1.0000
   3.250   0.6397   0.01939   0.01165  -0.0635   0.6468   1.0000
   3.500   0.6633   0.01963   0.01183  -0.0626   0.6403   1.0000
   3.750   0.6796   0.02019   0.01244  -0.0610   0.6312   1.0000
   4.000   0.7053   0.02039   0.01261  -0.0603   0.6247   1.0000
   4.250   0.7221   0.02096   0.01326  -0.0587   0.6151   1.0000
   4.500   0.7492   0.02112   0.01338  -0.0583   0.6082   1.0000
   4.750   0.7671   0.02164   0.01400  -0.0568   0.5981   1.0000
   5.000   0.7899   0.02197   0.01437  -0.0558   0.5894   1.0000
   5.250   0.8153   0.02213   0.01455  -0.0550   0.5805   1.0000
   5.500   0.8352   0.02256   0.01508  -0.0537   0.5702   1.0000
   5.750   0.8625   0.02262   0.01514  -0.0532   0.5614   1.0000
   6.000   0.8856   0.02279   0.01539  -0.0521   0.5505   1.0000
   6.250   0.9069   0.02305   0.01574  -0.0508   0.5390   1.0000
   6.500   0.9316   0.02309   0.01585  -0.0499   0.5278   1.0000
   6.750   0.9595   0.02291   0.01566  -0.0492   0.5164   1.0000
   7.000   0.9847   0.02278   0.01558  -0.0482   0.5036   1.0000
   7.250   1.0071   0.02274   0.01562  -0.0468   0.4894   1.0000
   7.500   1.0301   0.02259   0.01555  -0.0455   0.4744   1.0000
   7.750   1.0538   0.02236   0.01535  -0.0442   0.4583   1.0000
   8.000   1.0720   0.02230   0.01543  -0.0422   0.4397   1.0000
   8.250   1.0903   0.02218   0.01540  -0.0402   0.4192   1.0000
   8.500   1.1081   0.02205   0.01530  -0.0380   0.3965   1.0000
   8.750   1.1220   0.02208   0.01535  -0.0354   0.3692   1.0000
   9.000   1.1309   0.02240   0.01570  -0.0322   0.3357   1.0000
   9.250   1.1358   0.02300   0.01616  -0.0285   0.2974   1.0000
   9.500   1.1358   0.02404   0.01700  -0.0245   0.2577   1.0000
   9.750   1.1308   0.02540   0.01806  -0.0201   0.2249   1.0000
  10.000   1.1245   0.02697   0.01942  -0.0157   0.1974   1.0000
  10.250   1.1197   0.02871   0.02100  -0.0120   0.1735   1.0000
  10.500   1.1156   0.03061   0.02270  -0.0089   0.1543   1.0000
  10.750   1.1142   0.03257   0.02458  -0.0064   0.1368   1.0000
  11.000   1.1142   0.03459   0.02654  -0.0042   0.1217   1.0000
  11.250   1.1163   0.03667   0.02854  -0.0024   0.1086   1.0000
  11.500   1.1212   0.03876   0.03054  -0.0009   0.0971   1.0000
  11.750   1.1307   0.04083   0.03244   0.0004   0.0864   1.0000
  12.000   1.1338   0.04295   0.03479   0.0018   0.0789   1.0000
  12.250   1.1484   0.04510   0.03689   0.0028   0.0717   1.0000
  12.500   1.1530   0.04728   0.03920   0.0038   0.0661   1.0000
  12.750   1.1719   0.04978   0.04170   0.0046   0.0607   1.0000
  13.000   1.1734   0.05232   0.04453   0.0057   0.0572   1.0000
  13.250   1.1786   0.05467   0.04693   0.0063   0.0536   1.0000
  13.500   1.1953   0.05827   0.05061   0.0069   0.0507   1.0000
  13.750   1.1874   0.06169   0.05438   0.0077   0.0496   1.0000
  14.000   1.1778   0.06545   0.05846   0.0080   0.0487   1.0000
  14.250   1.1665   0.06953   0.06282   0.0078   0.0479   1.0000
  14.500   1.1527   0.07393   0.06748   0.0072   0.0470   1.0000
  14.750   1.1371   0.07874   0.07255   0.0061   0.0464   1.0000
  15.000   1.1186   0.08417   0.07822   0.0043   0.0461   1.0000
  15.250   1.0954   0.09051   0.08482   0.0017   0.0463   1.0000
  15.500   1.0654   0.09852   0.09310  -0.0022   0.0475   1.0000
  15.750   1.0360   0.10701   0.10181  -0.0069   0.0483   1.0000
  16.000   1.0060   0.11649   0.11147  -0.0124   0.0493   1.0000
  16.250   0.9792   0.12627   0.12137  -0.0182   0.0503   1.0000
  16.500   0.9566   0.13611   0.13124  -0.0238   0.0511   1.0000
<< Back to E209 (13.72%) (e209-il)

Polar data table (+)

Polar graphs


<< Back to E209 (13.72%) (e209-il)