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E226 (10.19%) (e226-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: E226 (10.19%) (e226-il)
Reynolds number: 500,000
Max Cl/Cd: 77.08 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e226-il-500000.txt
Download as CSV file: xf-e226-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.5827   0.10596   0.10363  -0.0094   1.0000   0.0256
 -11.000  -0.5833   0.10138   0.09907  -0.0116   1.0000   0.0262
  -8.500  -0.7628   0.03048   0.02578  -0.0325   1.0000   0.0177
  -8.250  -0.7511   0.02693   0.02208  -0.0308   1.0000   0.0167
  -8.000  -0.7379   0.02479   0.01968  -0.0287   1.0000   0.0166
  -7.750  -0.7245   0.02240   0.01702  -0.0265   1.0000   0.0161
  -7.500  -0.7096   0.02044   0.01484  -0.0244   1.0000   0.0157
  -7.250  -0.6940   0.01888   0.01310  -0.0222   1.0000   0.0154
  -7.000  -0.6784   0.01767   0.01176  -0.0200   1.0000   0.0154
  -6.750  -0.6630   0.01665   0.01065  -0.0178   1.0000   0.0156
  -6.500  -0.6476   0.01579   0.00970  -0.0156   1.0000   0.0159
  -6.250  -0.6211   0.01490   0.00872  -0.0157   0.9984   0.0161
  -6.000  -0.5861   0.01402   0.00776  -0.0175   0.9954   0.0166
  -5.750  -0.5517   0.01328   0.00695  -0.0191   0.9920   0.0171
  -5.500  -0.5168   0.01257   0.00616  -0.0208   0.9882   0.0177
  -5.250  -0.4811   0.01175   0.00528  -0.0228   0.9852   0.0195
  -5.000  -0.4464   0.01127   0.00475  -0.0243   0.9811   0.0212
  -4.750  -0.4108   0.01082   0.00423  -0.0260   0.9768   0.0238
  -4.500  -0.3752   0.00991   0.00360  -0.0279   0.9735   0.0728
  -4.250  -0.3431   0.00919   0.00323  -0.0292   0.9682   0.1458
  -4.000  -0.3116   0.00865   0.00297  -0.0303   0.9616   0.2100
  -3.750  -0.2802   0.00824   0.00275  -0.0312   0.9552   0.2641
  -3.500  -0.2521   0.00788   0.00257  -0.0313   0.9461   0.3163
  -3.250  -0.2250   0.00758   0.00241  -0.0311   0.9364   0.3624
  -3.000  -0.1986   0.00727   0.00226  -0.0307   0.9269   0.4169
  -2.750  -0.1742   0.00698   0.00216  -0.0299   0.9154   0.4741
  -2.500  -0.1491   0.00678   0.00206  -0.0292   0.9037   0.5161
  -2.250  -0.1236   0.00662   0.00196  -0.0285   0.8922   0.5524
  -2.000  -0.0982   0.00647   0.00188  -0.0278   0.8805   0.5880
  -1.750  -0.0727   0.00633   0.00181  -0.0270   0.8685   0.6234
  -1.500  -0.0471   0.00622   0.00176  -0.0263   0.8553   0.6581
  -1.250  -0.0215   0.00611   0.00171  -0.0256   0.8421   0.6907
  -1.000   0.0042   0.00602   0.00168  -0.0249   0.8287   0.7223
  -0.750   0.0299   0.00595   0.00165  -0.0242   0.8150   0.7525
  -0.500   0.0557   0.00590   0.00164  -0.0235   0.8009   0.7816
  -0.250   0.0814   0.00586   0.00163  -0.0227   0.7865   0.8094
   0.000   0.1070   0.00584   0.00163  -0.0220   0.7717   0.8356
   0.250   0.1325   0.00583   0.00165  -0.0211   0.7564   0.8602
   0.500   0.1582   0.00585   0.00166  -0.0203   0.7405   0.8839
   0.750   0.1842   0.00588   0.00169  -0.0196   0.7241   0.9055
   1.000   0.2112   0.00594   0.00172  -0.0191   0.7071   0.9258
   1.250   0.2405   0.00603   0.00176  -0.0191   0.6892   0.9430
   1.500   0.2724   0.00612   0.00180  -0.0197   0.6699   0.9572
   1.750   0.3085   0.00624   0.00185  -0.0213   0.6491   0.9666
   2.000   0.3447   0.00636   0.00191  -0.0230   0.6271   0.9749
   2.250   0.3827   0.00650   0.00196  -0.0252   0.6033   0.9819
   2.500   0.4218   0.00664   0.00202  -0.0276   0.5775   0.9873
   2.750   0.4604   0.00679   0.00208  -0.0300   0.5502   0.9930
   3.000   0.4998   0.00694   0.00214  -0.0326   0.5214   0.9980
   3.250   0.5291   0.00710   0.00221  -0.0331   0.4936   1.0000
   3.500   0.5506   0.00728   0.00230  -0.0319   0.4680   1.0000
   3.750   0.5724   0.00748   0.00241  -0.0308   0.4401   1.0000
   4.000   0.5941   0.00772   0.00254  -0.0297   0.4075   1.0000
   4.250   0.6159   0.00799   0.00270  -0.0286   0.3733   1.0000
   4.500   0.6375   0.00832   0.00287  -0.0275   0.3368   1.0000
   4.750   0.6592   0.00868   0.00308  -0.0264   0.2971   1.0000
   5.000   0.6808   0.00908   0.00331  -0.0254   0.2580   1.0000
   5.250   0.7024   0.00950   0.00358  -0.0243   0.2211   1.0000
   5.500   0.7242   0.00993   0.00386  -0.0233   0.1866   1.0000
   5.750   0.7459   0.01041   0.00418  -0.0223   0.1522   1.0000
   6.000   0.7674   0.01093   0.00454  -0.0214   0.1180   1.0000
   6.250   0.7889   0.01150   0.00494  -0.0204   0.0861   1.0000
   6.500   0.8094   0.01220   0.00544  -0.0193   0.0507   1.0000
   6.750   0.8282   0.01317   0.00619  -0.0179   0.0220   1.0000
   7.000   0.8505   0.01372   0.00677  -0.0170   0.0185   1.0000
   7.250   0.8717   0.01444   0.00755  -0.0158   0.0165   1.0000
   7.500   0.8936   0.01503   0.00823  -0.0149   0.0157   1.0000
   7.750   0.9147   0.01570   0.00897  -0.0138   0.0148   1.0000
   8.000   0.9353   0.01640   0.00973  -0.0127   0.0141   1.0000
   8.250   0.9547   0.01721   0.01059  -0.0115   0.0134   1.0000
   8.500   0.9699   0.01847   0.01193  -0.0097   0.0128   1.0000
   8.750   0.9850   0.01976   0.01332  -0.0080   0.0125   1.0000
   9.000   1.0028   0.02076   0.01442  -0.0066   0.0124   1.0000
   9.250   1.0207   0.02173   0.01549  -0.0053   0.0122   1.0000
   9.500   1.0372   0.02291   0.01678  -0.0038   0.0121   1.0000
   9.750   1.0533   0.02417   0.01816  -0.0023   0.0118   1.0000
  10.000   1.0683   0.02560   0.01972  -0.0007   0.0117   1.0000
  10.250   1.0824   0.02718   0.02147   0.0009   0.0116   1.0000
  10.500   1.0946   0.02894   0.02341   0.0027   0.0114   1.0000
  10.750   1.1045   0.03098   0.02565   0.0046   0.0115   1.0000
  11.000   1.1098   0.03314   0.02802   0.0070   0.0116   1.0000
  11.250   1.1097   0.03549   0.03061   0.0100   0.0117   1.0000
  11.500   1.1052   0.03814   0.03350   0.0128   0.0118   1.0000
  11.750   1.0967   0.04114   0.03674   0.0154   0.0119   1.0000
  12.000   1.0861   0.04439   0.04021   0.0172   0.0121   1.0000
  12.250   1.0718   0.04835   0.04437   0.0183   0.0123   1.0000
  12.500   1.0558   0.05249   0.04872   0.0185   0.0123   1.0000
  12.750   1.0540   0.05627   0.05257   0.0185   0.0127   1.0000
  13.000   1.0435   0.05991   0.05637   0.0175   0.0128   1.0000
  13.250   1.0280   0.06473   0.06136   0.0154   0.0128   1.0000
  13.500   0.9093   0.06795   0.06496   0.0111   0.0128   1.0000
  13.750   0.8904   0.07494   0.07209   0.0075   0.0129   1.0000
  14.000   0.8700   0.08265   0.07996   0.0031   0.0130   1.0000
  14.250   0.8449   0.09170   0.08919  -0.0025   0.0131   1.0000
  14.500   0.7132   0.12457   0.12257  -0.0241   0.0143   1.0000
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