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E61 (5.64%) (e61-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: E61 (5.64%) (e61-il)
Reynolds number: 1,000,000
Max Cl/Cd: 214.83 at α=1.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e61-il-1000000.txt
Download as CSV file: xf-e61-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E61  (5.64%)                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.1825   0.10920   0.10748  -0.0670   0.9808   0.0045
  -9.000  -0.1721   0.10633   0.10461  -0.0687   0.9784   0.0047
  -8.750  -0.1590   0.10322   0.10151  -0.0712   0.9768   0.0048
  -8.500  -0.1443   0.10005   0.09834  -0.0742   0.9755   0.0050
  -8.250  -0.1287   0.09679   0.09508  -0.0775   0.9745   0.0053
  -8.000  -0.1118   0.09353   0.09182  -0.0810   0.9736   0.0058
  -7.750  -0.0934   0.09008   0.08837  -0.0850   0.9728   0.0065
  -7.500  -0.0726   0.08678   0.08507  -0.0897   0.9720   0.0069
  -5.750   0.0431   0.06222   0.06052  -0.1164   0.9486   0.0076
  -5.500   0.0553   0.05983   0.05813  -0.1175   0.9427   0.0078
  -5.250   0.0813   0.05661   0.05490  -0.1226   0.9397   0.0080
  -5.000   0.1146   0.05283   0.05110  -0.1299   0.9380   0.0083
  -4.750   0.1520   0.04895   0.04720  -0.1380   0.9368   0.0089
  -1.500   0.7647   0.00731   0.00294  -0.2260   0.9028   0.0184
  -1.250   0.8058   0.00660   0.00211  -0.2290   0.8965   0.0177
  -1.000   0.8386   0.00629   0.00170  -0.2301   0.8864   0.0182
  -0.750   0.8707   0.00613   0.00145  -0.2310   0.8761   0.0197
  -0.500   0.9014   0.00603   0.00124  -0.2316   0.8650   0.0209
  -0.250   0.9302   0.00603   0.00113  -0.2318   0.8530   0.0231
   0.000   0.9578   0.00606   0.00108  -0.2317   0.8408   0.0257
   0.250   0.9859   0.00599   0.00111  -0.2318   0.8284   0.0939
   0.500   1.0153   0.00571   0.00128  -0.2325   0.8158   0.3269
   0.750   1.0432   0.00558   0.00143  -0.2328   0.8030   0.4930
   1.000   1.0700   0.00514   0.00169  -0.2328   0.7907   0.8555
   1.250   1.0892   0.00507   0.00171  -0.2307   0.7782   1.0000
   1.500   1.1145   0.00521   0.00177  -0.2301   0.7648   1.0000
   1.750   1.1395   0.00536   0.00187  -0.2295   0.7506   1.0000
   2.000   1.1644   0.00551   0.00196  -0.2288   0.7364   1.0000
   2.250   1.1891   0.00567   0.00206  -0.2282   0.7218   1.0000
   2.500   1.2133   0.00586   0.00217  -0.2274   0.7056   1.0000
   2.750   1.2372   0.00604   0.00229  -0.2265   0.6861   1.0000
   3.000   1.2599   0.00628   0.00246  -0.2254   0.6636   1.0000
   3.250   1.2826   0.00654   0.00262  -0.2244   0.6379   1.0000
   3.500   1.3043   0.00685   0.00281  -0.2231   0.6073   1.0000
   3.750   1.3220   0.00743   0.00310  -0.2210   0.5476   1.0000
   4.000   1.3348   0.00849   0.00361  -0.2181   0.4451   1.0000
   4.250   1.3518   0.00936   0.00408  -0.2161   0.3695   1.0000
   4.500   1.3680   0.01034   0.00464  -0.2140   0.2880   1.0000
   4.750   1.3863   0.01115   0.00513  -0.2123   0.2274   1.0000
   5.000   1.4032   0.01208   0.00569  -0.2104   0.1631   1.0000
   5.250   1.4175   0.01327   0.00643  -0.2081   0.0878   1.0000
   5.500   1.4303   0.01465   0.00736  -0.2054   0.0188   1.0000
   5.750   1.4499   0.01533   0.00799  -0.2038   0.0061   1.0000
   6.000   1.4708   0.01585   0.00858  -0.2024   0.0050   1.0000
   6.250   1.4895   0.01655   0.00938  -0.2005   0.0041   1.0000
   6.500   1.5058   0.01746   0.01044  -0.1981   0.0037   1.0000
   6.750   1.5197   0.01853   0.01165  -0.1954   0.0036   1.0000
   7.000   1.5325   0.01964   0.01289  -0.1924   0.0036   1.0000
   7.250   1.5454   0.02073   0.01408  -0.1895   0.0037   1.0000
   7.500   1.5581   0.02183   0.01527  -0.1867   0.0037   1.0000
   7.750   1.5710   0.02291   0.01644  -0.1840   0.0038   1.0000
   8.000   1.5847   0.02396   0.01759  -0.1814   0.0039   1.0000
   8.250   1.5966   0.02531   0.01904  -0.1786   0.0039   1.0000
   8.500   1.6076   0.02687   0.02071  -0.1757   0.0039   1.0000
   8.750   1.6176   0.02908   0.02306  -0.1728   0.0038   1.0000
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