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E226 (10.19%) (e226-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: E226 (10.19%) (e226-il)
Reynolds number: 100,000
Max Cl/Cd: 44.24 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e226-il-100000-n5.txt
Download as CSV file: xf-e226-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E226  (10.19%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5021   0.09147   0.08669  -0.0181   1.0000   0.0255
 -10.750  -0.6711   0.07344   0.06821  -0.0319   1.0000   0.0217
 -10.500  -0.6836   0.06754   0.06227  -0.0363   1.0000   0.0215
 -10.250  -0.7026   0.06184   0.05644  -0.0406   1.0000   0.0214
 -10.000  -0.7186   0.05768   0.05216  -0.0421   1.0000   0.0212
  -9.750  -0.7345   0.05420   0.04850  -0.0414   1.0000   0.0211
  -9.500  -0.7474   0.05042   0.04440  -0.0404   1.0000   0.0213
  -9.250  -0.7515   0.04699   0.04064  -0.0392   1.0000   0.0213
  -9.000  -0.7526   0.04364   0.03682  -0.0377   1.0000   0.0216
  -8.750  -0.7472   0.04059   0.03347  -0.0364   1.0000   0.0220
  -8.500  -0.7376   0.03786   0.03045  -0.0350   1.0000   0.0222
  -8.250  -0.7253   0.03538   0.02766  -0.0336   1.0000   0.0224
  -8.000  -0.7108   0.03315   0.02515  -0.0322   1.0000   0.0226
  -7.750  -0.6948   0.03114   0.02290  -0.0309   1.0000   0.0230
  -7.500  -0.6776   0.02935   0.02091  -0.0295   1.0000   0.0234
  -7.250  -0.6599   0.02771   0.01909  -0.0281   1.0000   0.0240
  -7.000  -0.6419   0.02623   0.01746  -0.0266   1.0000   0.0247
  -6.750  -0.6241   0.02491   0.01599  -0.0250   1.0000   0.0254
  -6.500  -0.6064   0.02375   0.01469  -0.0234   1.0000   0.0267
  -6.250  -0.5894   0.02265   0.01350  -0.0217   1.0000   0.0286
  -6.000  -0.5723   0.02171   0.01253  -0.0202   1.0000   0.0307
  -5.750  -0.5549   0.02081   0.01153  -0.0185   1.0000   0.0330
  -5.250  -0.5204   0.01903   0.00956  -0.0151   1.0000   0.0401
  -5.000  -0.5030   0.01809   0.00863  -0.0134   1.0000   0.0521
  -4.750  -0.4859   0.01712   0.00790  -0.0118   1.0000   0.0882
  -4.500  -0.4683   0.01633   0.00741  -0.0105   1.0000   0.1441
  -4.000  -0.4297   0.01505   0.00679  -0.0086   0.9987   0.2835
  -3.750  -0.3951   0.01458   0.00655  -0.0105   0.9912   0.3520
  -3.500  -0.3593   0.01424   0.00635  -0.0124   0.9843   0.4085
  -3.250  -0.3255   0.01394   0.00614  -0.0138   0.9760   0.4609
  -3.000  -0.2910   0.01368   0.00600  -0.0152   0.9682   0.5118
  -2.750  -0.2559   0.01346   0.00589  -0.0166   0.9604   0.5617
  -2.500  -0.2221   0.01328   0.00578  -0.0177   0.9520   0.6084
  -2.250  -0.1855   0.01312   0.00570  -0.0191   0.9448   0.6535
  -2.000  -0.1535   0.01298   0.00563  -0.0196   0.9351   0.6947
  -1.750  -0.1177   0.01288   0.00557  -0.0207   0.9274   0.7346
  -1.500  -0.0864   0.01280   0.00554  -0.0208   0.9169   0.7707
  -1.250  -0.0542   0.01274   0.00549  -0.0211   0.9066   0.8046
  -1.000  -0.0185   0.01269   0.00544  -0.0220   0.8976   0.8355
  -0.750   0.0154   0.01267   0.00541  -0.0226   0.8861   0.8635
  -0.500   0.0518   0.01265   0.00537  -0.0237   0.8744   0.8884
  -0.250   0.0901   0.01262   0.00530  -0.0253   0.8627   0.9105
   0.000   0.1302   0.01259   0.00522  -0.0273   0.8502   0.9295
   0.250   0.1713   0.01255   0.00514  -0.0296   0.8367   0.9461
   0.500   0.2125   0.01250   0.00505  -0.0320   0.8216   0.9611
   0.750   0.2542   0.01245   0.00496  -0.0346   0.8050   0.9749
   1.000   0.2959   0.01238   0.00486  -0.0373   0.7870   0.9878
   1.250   0.3368   0.01231   0.00475  -0.0400   0.7680   1.0000
   1.500   0.3580   0.01232   0.00471  -0.0386   0.7490   1.0000
   1.750   0.3791   0.01236   0.00470  -0.0372   0.7290   1.0000
   2.000   0.4005   0.01243   0.00472  -0.0359   0.7085   1.0000
   2.500   0.4442   0.01262   0.00482  -0.0332   0.6659   1.0000
   2.750   0.4663   0.01274   0.00488  -0.0320   0.6439   1.0000
   3.000   0.4884   0.01289   0.00500  -0.0307   0.6201   1.0000
   3.250   0.5107   0.01307   0.00513  -0.0295   0.5963   1.0000
   3.500   0.5329   0.01327   0.00528  -0.0282   0.5711   1.0000
   3.750   0.5551   0.01349   0.00546  -0.0270   0.5445   1.0000
   4.000   0.5772   0.01374   0.00566  -0.0258   0.5170   1.0000
   4.250   0.5993   0.01402   0.00590  -0.0245   0.4883   1.0000
   4.500   0.6212   0.01433   0.00616  -0.0233   0.4582   1.0000
   4.750   0.6431   0.01468   0.00645  -0.0222   0.4271   1.0000
   5.000   0.6647   0.01507   0.00677  -0.0210   0.3950   1.0000
   5.250   0.6861   0.01551   0.00715  -0.0198   0.3619   1.0000
   5.500   0.7074   0.01599   0.00757  -0.0187   0.3273   1.0000
   5.750   0.7282   0.01653   0.00802  -0.0176   0.2915   1.0000
   6.000   0.7487   0.01713   0.00853  -0.0165   0.2560   1.0000
   6.250   0.7692   0.01777   0.00913  -0.0154   0.2217   1.0000
   6.500   0.7887   0.01853   0.00976  -0.0142   0.1861   1.0000
   6.750   0.8073   0.01941   0.01044  -0.0131   0.1453   1.0000
   7.000   0.8255   0.02040   0.01119  -0.0120   0.1053   1.0000
   7.250   0.8437   0.02141   0.01210  -0.0109   0.0754   1.0000
   7.500   0.8607   0.02260   0.01318  -0.0096   0.0522   1.0000
   7.750   0.8766   0.02391   0.01446  -0.0080   0.0383   1.0000
   8.000   0.8915   0.02529   0.01589  -0.0064   0.0325   1.0000
   8.250   0.9067   0.02657   0.01730  -0.0047   0.0292   1.0000
   8.500   0.9200   0.02799   0.01880  -0.0031   0.0273   1.0000
   8.750   0.9336   0.02944   0.02041  -0.0013   0.0258   1.0000
   9.000   0.9476   0.03087   0.02202   0.0003   0.0241   1.0000
   9.250   0.9610   0.03227   0.02353   0.0018   0.0226   1.0000
   9.500   0.9722   0.03380   0.02512   0.0033   0.0214   1.0000
   9.750   0.9836   0.03558   0.02704   0.0049   0.0206   1.0000
  10.000   0.9951   0.03752   0.02921   0.0066   0.0200   1.0000
  10.250   1.0046   0.03956   0.03147   0.0083   0.0196   1.0000
  10.500   1.0114   0.04178   0.03396   0.0101   0.0193   1.0000
  10.750   1.0150   0.04423   0.03667   0.0120   0.0189   1.0000
  11.000   1.0157   0.04683   0.03952   0.0137   0.0187   1.0000
  11.250   1.0129   0.04969   0.04265   0.0152   0.0186   1.0000
  11.500   1.0064   0.05290   0.04612   0.0162   0.0184   1.0000
  11.750   0.9972   0.05647   0.04995   0.0165   0.0183   1.0000
  12.000   0.9847   0.06063   0.05438   0.0160   0.0183   1.0000
  12.250   0.9696   0.06544   0.05943   0.0144   0.0184   1.0000
  12.500   0.9515   0.07113   0.06535   0.0116   0.0184   1.0000
  12.750   0.9304   0.07797   0.07241   0.0075   0.0185   1.0000
  13.000   0.9072   0.08604   0.08069   0.0021   0.0187   1.0000
  13.250   0.8805   0.09590   0.09072  -0.0047   0.0191   1.0000
  13.500   0.8506   0.10783   0.10275  -0.0127   0.0195   1.0000
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