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E216 (10.4%) (e216-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E216 (10.4%) (e216-il)
Reynolds number: 100,000
Max Cl/Cd: 68.5 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e216-il-100000.txt
Download as CSV file: xf-e216-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E216  (10.4%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -6.750  -0.3889   0.10382   0.09960  -0.0197   1.0000   0.1018
  -6.500  -0.4111   0.10310   0.09899  -0.0179   1.0000   0.1034
  -6.250  -0.4341   0.10190   0.09790  -0.0212   1.0000   0.1046
  -6.000  -0.4393   0.09802   0.09410  -0.0226   1.0000   0.1060
  -5.750  -0.4298   0.09566   0.09175  -0.0156   1.0000   0.1084
  -5.500  -0.4287   0.09346   0.08958  -0.0140   1.0000   0.1114
  -5.250  -0.4247   0.08715   0.08327  -0.0376   1.0000   0.1199
  -5.000  -0.4265   0.08498   0.08118  -0.0292   1.0000   0.1209
  -4.750  -0.4245   0.08313   0.07936  -0.0238   1.0000   0.1227
  -4.500  -0.4020   0.07823   0.07439  -0.0361   1.0000   0.1338
  -4.250  -0.3900   0.07409   0.07027  -0.0373   0.9990   0.1368
  -4.000  -0.2319   0.04133   0.03529  -0.0917   1.0000   0.0636
  -3.750  -0.1694   0.03563   0.02897  -0.1016   0.9974   0.0606
  -3.500  -0.1056   0.03261   0.02502  -0.1096   0.9937   0.0629
  -3.250  -0.0531   0.03017   0.02212  -0.1151   0.9896   0.0663
  -3.000  -0.0035   0.02900   0.02072  -0.1193   0.9860   0.0726
  -2.750   0.0408   0.02799   0.01962  -0.1228   0.9801   0.0884
  -2.500   0.0924   0.02687   0.01870  -0.1278   0.9766   0.1499
  -2.250   0.1361   0.02658   0.01872  -0.1318   0.9701   0.2422
  -2.000   0.1813   0.02655   0.01893  -0.1356   0.9649   0.3221
  -1.750   0.2177   0.02657   0.01910  -0.1377   0.9567   0.3868
  -1.500   0.2582   0.02672   0.01937  -0.1403   0.9505   0.4498
  -1.250   0.2943   0.02681   0.01957  -0.1420   0.9424   0.5042
  -1.000   0.3285   0.02693   0.01976  -0.1432   0.9343   0.5557
  -0.750   0.3681   0.02699   0.01991  -0.1452   0.9279   0.6077
  -0.500   0.3976   0.02706   0.02007  -0.1454   0.9184   0.6532
  -0.250   0.4375   0.02699   0.02007  -0.1471   0.9130   0.7031
   0.000   0.4616   0.02699   0.02014  -0.1461   0.9022   0.7469
   0.250   0.4884   0.02687   0.02009  -0.1453   0.8936   0.7942
   0.500   0.5148   0.02651   0.01979  -0.1441   0.8858   0.8497
   0.750   0.5249   0.02598   0.01939  -0.1401   0.8742   0.9404
   1.000   0.5842   0.02565   0.01887  -0.1465   0.8696   1.0000
   1.250   0.6201   0.02580   0.01890  -0.1487   0.8584   1.0000
   1.500   0.6715   0.02544   0.01842  -0.1528   0.8537   1.0000
   1.750   0.7053   0.02546   0.01838  -0.1541   0.8428   1.0000
   2.000   0.7418   0.02535   0.01822  -0.1556   0.8332   1.0000
   2.250   0.7892   0.02473   0.01756  -0.1585   0.8274   1.0000
   2.500   0.8244   0.02449   0.01732  -0.1595   0.8173   1.0000
   2.750   0.8744   0.02353   0.01636  -0.1625   0.8124   1.0000
   3.000   0.9109   0.02314   0.01599  -0.1635   0.8021   1.0000
   3.250   0.9650   0.02202   0.01493  -0.1672   0.7969   1.0000
   3.500   1.0026   0.02159   0.01454  -0.1684   0.7852   1.0000
   3.750   1.0517   0.02080   0.01379  -0.1714   0.7758   1.0000
   4.000   1.1030   0.01992   0.01298  -0.1747   0.7654   1.0000
   4.250   1.1424   0.01950   0.01259  -0.1761   0.7504   1.0000
   4.500   1.1794   0.01920   0.01234  -0.1770   0.7335   1.0000
   4.750   1.2089   0.01917   0.01234  -0.1767   0.7136   1.0000
   5.000   1.2420   0.01908   0.01225  -0.1770   0.6935   1.0000
   5.250   1.2758   0.01904   0.01221  -0.1775   0.6726   1.0000
   5.500   1.3002   0.01926   0.01244  -0.1763   0.6489   1.0000
   5.750   1.3276   0.01944   0.01259  -0.1756   0.6251   1.0000
   6.000   1.3516   0.01973   0.01285  -0.1744   0.5997   1.0000
   6.250   1.3729   0.02012   0.01324  -0.1728   0.5735   1.0000
   6.500   1.3944   0.02054   0.01361  -0.1712   0.5471   1.0000
   6.750   1.4149   0.02102   0.01401  -0.1694   0.5202   1.0000
   7.000   1.4317   0.02158   0.01456  -0.1671   0.4920   1.0000
   7.250   1.4473   0.02219   0.01515  -0.1646   0.4634   1.0000
   7.500   1.4616   0.02287   0.01578  -0.1619   0.4345   1.0000
   7.750   1.4744   0.02363   0.01648  -0.1590   0.4055   1.0000
   8.000   1.4856   0.02446   0.01725  -0.1559   0.3766   1.0000
   8.250   1.4948   0.02537   0.01810  -0.1526   0.3481   1.0000
   8.500   1.5019   0.02638   0.01901  -0.1489   0.3208   1.0000
   8.750   1.5075   0.02749   0.02004  -0.1452   0.2936   1.0000
   9.000   1.5122   0.02871   0.02123  -0.1414   0.2667   1.0000
   9.250   1.5152   0.03007   0.02251  -0.1376   0.2403   1.0000
   9.500   1.5164   0.03156   0.02390  -0.1338   0.2153   1.0000
   9.750   1.5162   0.03316   0.02541  -0.1300   0.1910   1.0000
  10.000   1.5165   0.03487   0.02713  -0.1265   0.1670   1.0000
  10.250   1.5155   0.03690   0.02903  -0.1232   0.1473   1.0000
  10.500   1.5161   0.03902   0.03119  -0.1201   0.1268   1.0000
  10.750   1.5132   0.04150   0.03361  -0.1170   0.1089   1.0000
  11.000   1.5084   0.04443   0.03645  -0.1140   0.0922   1.0000
  11.250   1.5047   0.04757   0.03960  -0.1112   0.0773   1.0000
  11.500   1.5039   0.05078   0.04274  -0.1087   0.0674   1.0000
  11.750   1.5077   0.05356   0.04558  -0.1068   0.0602   1.0000
  12.000   1.5168   0.05643   0.04854  -0.1051   0.0547   1.0000
  12.250   1.5238   0.05905   0.05128  -0.1037   0.0505   1.0000
  12.500   1.5461   0.06198   0.05417  -0.1029   0.0470   1.0000
  12.750   1.5571   0.06504   0.05758  -0.1015   0.0452   1.0000
  13.000   1.5663   0.06846   0.06131  -0.1002   0.0439   1.0000
  13.250   1.5706   0.07220   0.06536  -0.0988   0.0428   1.0000
  13.500   1.5706   0.07612   0.06958  -0.0975   0.0420   1.0000
  13.750   1.5659   0.08030   0.07405  -0.0964   0.0413   1.0000
  14.000   1.5581   0.08470   0.07871  -0.0956   0.0407   1.0000
  14.250   1.5491   0.08918   0.08343  -0.0952   0.0401   1.0000
  14.500   1.5397   0.09401   0.08847  -0.0952   0.0395   1.0000
  14.750   1.5258   0.09940   0.09412  -0.0958   0.0393   1.0000
  15.000   1.5057   0.10547   0.10051  -0.0972   0.0394   1.0000
  15.250   1.4873   0.11178   0.10708  -0.0993   0.0392   1.0000
  15.500   1.4508   0.12120   0.11695  -0.1042   0.0403   1.0000
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