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E209 (13.72%) (e209-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: E209 (13.72%) (e209-il)
Reynolds number: 50,000
Max Cl/Cd: 29.39 at α=10°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e209-il-50000.txt
Download as CSV file: xf-e209-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3855   0.10888   0.10183  -0.0178   1.0000   0.3044
  -9.500  -0.4970   0.08481   0.07816  -0.0441   1.0000   0.1389
  -9.250  -0.5145   0.07783   0.07125  -0.0479   1.0000   0.1326
  -9.000  -0.6098   0.06984   0.06321  -0.0518   1.0000   0.1224
  -8.750  -0.6099   0.06552   0.05889  -0.0508   1.0000   0.1210
  -8.500  -0.6193   0.06136   0.05462  -0.0495   1.0000   0.1194
  -8.250  -0.6304   0.05726   0.05034  -0.0479   1.0000   0.1178
  -8.000  -0.6396   0.05324   0.04605  -0.0458   1.0000   0.1166
  -7.750  -0.6435   0.04963   0.04211  -0.0436   1.0000   0.1165
  -7.500  -0.6436   0.04638   0.03849  -0.0413   1.0000   0.1182
  -7.250  -0.6414   0.04337   0.03499  -0.0388   1.0000   0.1207
  -7.000  -0.6353   0.04048   0.03164  -0.0364   1.0000   0.1233
  -6.750  -0.6210   0.03795   0.02912  -0.0346   1.0000   0.1278
  -6.500  -0.6092   0.03584   0.02667  -0.0324   1.0000   0.1343
  -6.250  -0.5957   0.03387   0.02463  -0.0305   1.0000   0.1433
  -6.000  -0.5811   0.03189   0.02243  -0.0285   1.0000   0.1538
  -5.750  -0.5669   0.03032   0.02091  -0.0266   1.0000   0.1702
  -5.500  -0.5530   0.02879   0.01937  -0.0245   1.0000   0.1935
  -5.250  -0.5404   0.02729   0.01815  -0.0224   1.0000   0.2275
  -5.000  -0.5295   0.02598   0.01727  -0.0201   1.0000   0.2778
  -4.750  -0.5204   0.02511   0.01700  -0.0173   1.0000   0.3477
  -4.500  -0.5125   0.02517   0.01755  -0.0136   1.0000   0.4242
  -4.250  -0.5046   0.02559   0.01821  -0.0096   1.0000   0.4920
  -4.000  -0.4963   0.02605   0.01878  -0.0055   1.0000   0.5446
  -3.750  -0.4879   0.02644   0.01922  -0.0015   1.0000   0.5893
  -3.500  -0.4798   0.02680   0.01963   0.0028   1.0000   0.6266
  -3.250  -0.4713   0.02699   0.01979   0.0065   1.0000   0.6624
  -3.000  -0.4597   0.02719   0.01994   0.0097   0.9986   0.6966
  -2.750  -0.4270   0.02790   0.02054   0.0100   0.9864   0.7352
  -2.500  -0.3959   0.02835   0.02084   0.0099   0.9745   0.7715
  -2.250  -0.3663   0.02870   0.02106   0.0100   0.9631   0.8037
  -2.000  -0.3331   0.02907   0.02127   0.0095   0.9518   0.8347
  -1.750  -0.2894   0.02958   0.02161   0.0070   0.9415   0.8652
  -1.500  -0.2371   0.03011   0.02193   0.0025   0.9306   0.8933
  -1.250  -0.1581   0.03089   0.02245  -0.0072   0.9207   0.9183
  -1.000  -0.0575   0.03156   0.02279  -0.0215   0.9118   0.9404
  -0.750   0.0341   0.03181   0.02281  -0.0348   0.9015   0.9593
  -0.500   0.1192   0.03184   0.02266  -0.0474   0.8918   0.9784
  -0.250   0.2217   0.03146   0.02212  -0.0629   0.8836   0.9963
   0.000   0.2360   0.03158   0.02218  -0.0637   0.8713   1.0000
   0.250   0.2281   0.03180   0.02236  -0.0608   0.8591   1.0000
   0.500   0.2172   0.03195   0.02245  -0.0574   0.8479   1.0000
   0.750   0.2179   0.03210   0.02250  -0.0553   0.8382   1.0000
   1.000   0.1999   0.03270   0.02293  -0.0501   0.8272   1.0000
   1.250   0.2178   0.03340   0.02348  -0.0499   0.8182   1.0000
   1.500   0.2408   0.03413   0.02409  -0.0503   0.8092   1.0000
   1.750   0.2502   0.03510   0.02496  -0.0489   0.7998   1.0000
   2.000   0.2897   0.03578   0.02557  -0.0514   0.7920   1.0000
   2.250   0.2882   0.03703   0.02672  -0.0485   0.7825   1.0000
   2.500   0.3179   0.03792   0.02757  -0.0496   0.7744   1.0000
   2.750   0.3266   0.03914   0.02875  -0.0482   0.7657   1.0000
   3.000   0.3470   0.04026   0.02983  -0.0482   0.7575   1.0000
   3.250   0.3649   0.04144   0.03099  -0.0479   0.7491   1.0000
   3.500   0.3774   0.04280   0.03232  -0.0470   0.7408   1.0000
   3.750   0.4038   0.04390   0.03343  -0.0477   0.7325   1.0000
   4.000   0.4078   0.04551   0.03504  -0.0460   0.7241   1.0000
   4.250   0.4483   0.04641   0.03599  -0.0480   0.7154   1.0000
   4.500   0.4394   0.04836   0.03791  -0.0453   0.7067   1.0000
   4.750   0.4649   0.04965   0.03924  -0.0457   0.6975   1.0000
   5.000   0.4785   0.05117   0.04081  -0.0451   0.6879   1.0000
   5.250   0.4871   0.05290   0.04257  -0.0442   0.6784   1.0000
   5.500   0.5151   0.05414   0.04389  -0.0446   0.6675   1.0000
   5.750   0.5320   0.05565   0.04546  -0.0443   0.6564   1.0000
   6.000   0.5361   0.05758   0.04746  -0.0431   0.6453   1.0000
   6.250   0.5530   0.05917   0.04912  -0.0426   0.6331   1.0000
   6.500   0.5745   0.06058   0.05063  -0.0424   0.6199   1.0000
   6.750   0.5969   0.06193   0.05208  -0.0421   0.6059   1.0000
   7.000   0.6186   0.06326   0.05354  -0.0416   0.5915   1.0000
   7.250   0.6368   0.06467   0.05506  -0.0409   0.5762   1.0000
   7.500   0.6526   0.06617   0.05668  -0.0401   0.5606   1.0000
   7.750   0.6661   0.06777   0.05839  -0.0391   0.5443   1.0000
   8.000   0.6797   0.06936   0.06011  -0.0381   0.5273   1.0000
   8.250   0.6972   0.07066   0.06154  -0.0371   0.5097   1.0000
   8.500   0.7324   0.07048   0.06157  -0.0358   0.4906   1.0000
   8.750   0.7667   0.07003   0.06136  -0.0341   0.4714   1.0000
   9.000   0.7645   0.07268   0.06408  -0.0330   0.4530   1.0000
   9.250   0.7963   0.07191   0.06353  -0.0309   0.4323   1.0000
   9.500   0.8451   0.06864   0.06058  -0.0276   0.4105   1.0000
   9.750   1.1138   0.03889   0.03142  -0.0220   0.3315   1.0000
  10.000   1.1288   0.03841   0.03062  -0.0184   0.2920   1.0000
  10.250   1.1334   0.03936   0.03131  -0.0149   0.2592   1.0000
  10.500   1.1380   0.04089   0.03258  -0.0117   0.2301   1.0000
  10.750   1.1431   0.04281   0.03430  -0.0089   0.2051   1.0000
  11.000   1.1574   0.04505   0.03622  -0.0073   0.1804   1.0000
  11.250   1.1612   0.04762   0.03885  -0.0050   0.1643   1.0000
  11.500   1.1677   0.05033   0.04159  -0.0030   0.1499   1.0000
  11.750   1.1785   0.05332   0.04461  -0.0017   0.1374   1.0000
  12.000   1.1763   0.05617   0.04766   0.0006   0.1294   1.0000
  12.250   1.1769   0.05968   0.05134   0.0022   0.1232   1.0000
  12.500   1.1606   0.06335   0.05535   0.0044   0.1206   1.0000
  12.750   1.1795   0.06682   0.05872   0.0047   0.1119   1.0000
  13.000   1.1560   0.07084   0.06307   0.0063   0.1113   1.0000
  13.250   1.1309   0.07553   0.06804   0.0067   0.1111   1.0000
  13.500   1.1050   0.08089   0.07364   0.0061   0.1113   1.0000
  13.750   1.0774   0.08704   0.07999   0.0045   0.1117   1.0000
  14.000   1.0508   0.09386   0.08697   0.0021   0.1123   1.0000
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