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E226 (10.19%) (e226-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E226 (10.19%) (e226-il)
Reynolds number: 100,000
Max Cl/Cd: 45.26 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e226-il-100000.txt
Download as CSV file: xf-e226-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.6144   0.05331   0.04851  -0.0398   1.0000   0.0726
  -8.500  -0.6669   0.05961   0.05445  -0.0380   1.0000   0.0710
  -8.250  -0.6905   0.05168   0.04575  -0.0373   1.0000   0.0601
  -8.000  -0.6852   0.04738   0.04125  -0.0363   1.0000   0.0589
  -7.750  -0.6800   0.04345   0.03698  -0.0348   1.0000   0.0583
  -7.500  -0.6718   0.03975   0.03291  -0.0331   1.0000   0.0572
  -7.250  -0.6617   0.03616   0.02884  -0.0311   1.0000   0.0558
  -7.000  -0.6487   0.03291   0.02511  -0.0291   1.0000   0.0546
  -6.750  -0.6327   0.03020   0.02196  -0.0271   1.0000   0.0542
  -6.500  -0.6142   0.02793   0.01937  -0.0254   1.0000   0.0546
  -6.250  -0.5941   0.02600   0.01720  -0.0238   1.0000   0.0557
  -6.000  -0.5735   0.02428   0.01531  -0.0222   1.0000   0.0577
  -5.750  -0.5530   0.02297   0.01379  -0.0205   1.0000   0.0612
  -5.500  -0.5353   0.02139   0.01235  -0.0189   1.0000   0.0675
  -5.250  -0.5173   0.02007   0.01100  -0.0169   1.0000   0.0750
  -5.000  -0.5019   0.01865   0.00973  -0.0147   1.0000   0.0908
  -4.750  -0.4900   0.01657   0.00834  -0.0123   1.0000   0.1796
  -4.500  -0.4743   0.01568   0.00787  -0.0107   1.0000   0.2692
  -4.250  -0.4581   0.01515   0.00767  -0.0089   1.0000   0.3476
  -4.000  -0.4414   0.01472   0.00749  -0.0071   1.0000   0.4136
  -3.750  -0.4239   0.01435   0.00731  -0.0052   1.0000   0.4709
  -3.500  -0.4061   0.01406   0.00719  -0.0033   1.0000   0.5265
  -3.250  -0.3885   0.01383   0.00711  -0.0012   1.0000   0.5801
  -3.000  -0.3712   0.01366   0.00710   0.0010   1.0000   0.6318
  -2.750  -0.3545   0.01355   0.00713   0.0034   1.0000   0.6824
  -2.500  -0.3383   0.01349   0.00719   0.0059   1.0000   0.7334
  -2.250  -0.3229   0.01349   0.00729   0.0088   1.0000   0.7832
  -2.000  -0.3075   0.01354   0.00743   0.0117   1.0000   0.8355
  -1.750  -0.2841   0.01370   0.00763   0.0132   1.0000   0.8914
  -1.500  -0.2289   0.01407   0.00789   0.0083   1.0000   0.9456
  -1.250  -0.1493   0.01449   0.00809  -0.0019   1.0000   0.9821
  -1.000  -0.0960   0.01458   0.00801  -0.0086   0.9985   1.0000
  -0.750  -0.0407   0.01477   0.00805  -0.0154   0.9868   1.0000
  -0.500   0.0124   0.01492   0.00808  -0.0214   0.9749   1.0000
  -0.250   0.0643   0.01501   0.00809  -0.0270   0.9626   1.0000
   0.000   0.1169   0.01505   0.00807  -0.0324   0.9504   1.0000
   0.250   0.1742   0.01502   0.00801  -0.0384   0.9398   1.0000
   0.500   0.2328   0.01486   0.00785  -0.0444   0.9291   1.0000
   0.750   0.2804   0.01466   0.00767  -0.0481   0.9149   1.0000
   1.000   0.3224   0.01444   0.00746  -0.0505   0.8994   1.0000
   1.250   0.3552   0.01427   0.00730  -0.0510   0.8816   1.0000
   1.500   0.3802   0.01418   0.00723  -0.0501   0.8616   1.0000
   1.750   0.4049   0.01407   0.00711  -0.0487   0.8424   1.0000
   2.000   0.4284   0.01396   0.00698  -0.0471   0.8238   1.0000
   2.250   0.4474   0.01398   0.00700  -0.0448   0.8017   1.0000
   2.500   0.4689   0.01394   0.00694  -0.0428   0.7812   1.0000
   2.750   0.4894   0.01396   0.00695  -0.0407   0.7590   1.0000
   3.000   0.5108   0.01397   0.00693  -0.0387   0.7368   1.0000
   3.250   0.5318   0.01404   0.00698  -0.0368   0.7127   1.0000
   3.500   0.5539   0.01410   0.00700  -0.0349   0.6891   1.0000
   3.750   0.5753   0.01421   0.00708  -0.0331   0.6626   1.0000
   4.000   0.5968   0.01435   0.00719  -0.0313   0.6350   1.0000
   4.250   0.6185   0.01452   0.00731  -0.0296   0.6061   1.0000
   4.500   0.6401   0.01472   0.00748  -0.0279   0.5758   1.0000
   4.750   0.6616   0.01496   0.00765  -0.0262   0.5440   1.0000
   5.000   0.6828   0.01525   0.00788  -0.0246   0.5101   1.0000
   5.250   0.7035   0.01559   0.00818  -0.0229   0.4733   1.0000
   5.500   0.7237   0.01599   0.00848  -0.0212   0.4348   1.0000
   5.750   0.7433   0.01648   0.00883  -0.0196   0.3942   1.0000
   6.000   0.7623   0.01706   0.00928  -0.0179   0.3511   1.0000
   6.250   0.7806   0.01776   0.00985  -0.0162   0.3065   1.0000
   6.500   0.7981   0.01861   0.01054  -0.0146   0.2613   1.0000
   6.750   0.8145   0.01952   0.01127  -0.0129   0.2141   1.0000
   7.000   0.8297   0.02047   0.01198  -0.0113   0.1662   1.0000
   7.250   0.8435   0.02188   0.01313  -0.0095   0.1232   1.0000
   7.500   0.8549   0.02384   0.01483  -0.0072   0.0845   1.0000
   7.750   0.8694   0.02588   0.01679  -0.0052   0.0670   1.0000
   8.000   0.8882   0.02778   0.01859  -0.0038   0.0595   1.0000
   8.250   0.9108   0.03004   0.02100  -0.0027   0.0554   1.0000
   8.500   0.9320   0.03194   0.02308  -0.0017   0.0513   1.0000
   8.750   0.9526   0.03442   0.02551  -0.0011   0.0478   1.0000
   9.000   0.9708   0.03726   0.02869   0.0001   0.0464   1.0000
   9.250   0.9857   0.04016   0.03205   0.0018   0.0458   1.0000
   9.500   0.9965   0.04338   0.03569   0.0035   0.0456   1.0000
   9.750   1.0025   0.04693   0.03968   0.0055   0.0456   1.0000
  10.000   1.0047   0.05070   0.04382   0.0075   0.0459   1.0000
  10.250   1.0031   0.05468   0.04814   0.0094   0.0463   1.0000
  10.500   0.9978   0.05904   0.05277   0.0111   0.0468   1.0000
  10.750   0.9943   0.06374   0.05768   0.0123   0.0474   1.0000
  11.000   0.9778   0.06554   0.05979   0.0153   0.0481   1.0000
  11.250   0.9367   0.06965   0.06429   0.0164   0.0492   1.0000
  11.500   0.8891   0.07695   0.07190   0.0125   0.0504   1.0000
  11.750   0.8413   0.08780   0.08291   0.0041   0.0518   1.0000
  12.000   0.7984   0.10242   0.09755  -0.0067   0.0546   1.0000
  12.250   0.7851   0.11131   0.10640  -0.0112   0.0566   1.0000
  12.500   0.7906   0.11464   0.10972  -0.0108   0.0579   1.0000
  12.750   0.6191   0.13005   0.12543  -0.0170   0.0816   1.0000
  13.000   0.6085   0.14343   0.13883  -0.0224   0.1218   1.0000
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