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E221 (9.39%) (e221-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: E221 (9.39%) (e221-il)
Reynolds number: 50,000
Max Cl/Cd: 29.42 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e221-il-50000.txt
Download as CSV file: xf-e221-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E221  (9.39%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5169   0.12196   0.11528   0.0125   1.0000   0.2098
  -9.500  -0.5083   0.11761   0.11097   0.0121   1.0000   0.2161
  -9.250  -0.5177   0.11584   0.10929   0.0100   1.0000   0.2255
  -9.000  -0.4977   0.11056   0.10398   0.0110   1.0000   0.2342
  -8.750  -0.5060   0.10805   0.10159   0.0091   1.0000   0.2424
  -8.500  -0.5045   0.10516   0.09874   0.0085   1.0000   0.2544
  -8.250  -0.4877   0.10048   0.09408   0.0093   1.0000   0.2654
  -8.000  -0.4831   0.09694   0.09060   0.0091   1.0000   0.2761
  -7.750  -0.4823   0.09374   0.08748   0.0087   1.0000   0.2886
  -7.500  -0.4774   0.09038   0.08419   0.0090   1.0000   0.3038
  -7.250  -0.4706   0.08711   0.08097   0.0097   1.0000   0.3221
  -7.000  -0.4790   0.08487   0.07885   0.0099   1.0000   0.3418
  -6.000  -0.4995   0.05532   0.04852  -0.0235   1.0000   0.1375
  -5.750  -0.4878   0.04982   0.04261  -0.0239   1.0000   0.1218
  -5.500  -0.4774   0.04506   0.03699  -0.0232   1.0000   0.1111
  -5.250  -0.4618   0.04153   0.03319  -0.0220   1.0000   0.1103
  -5.000  -0.4459   0.03835   0.02965  -0.0205   1.0000   0.1098
  -4.750  -0.4293   0.03542   0.02630  -0.0188   1.0000   0.1097
  -4.500  -0.4114   0.03270   0.02316  -0.0169   1.0000   0.1100
  -4.250  -0.3928   0.03040   0.02040  -0.0149   1.0000   0.1118
  -4.000  -0.3751   0.02841   0.01845  -0.0133   1.0000   0.1208
  -3.750  -0.3564   0.02658   0.01640  -0.0115   1.0000   0.1306
  -3.500  -0.3374   0.02496   0.01473  -0.0097   1.0000   0.1476
  -3.250  -0.3175   0.02337   0.01318  -0.0081   1.0000   0.1812
  -3.000  -0.0918   0.01730   0.00976  -0.0332   1.0000   1.0000
  -2.750  -0.0870   0.01698   0.00922  -0.0313   1.0000   1.0000
  -2.500  -0.0867   0.01693   0.00901  -0.0282   1.0000   1.0000
  -2.250  -0.0914   0.01710   0.00900  -0.0242   1.0000   1.0000
  -2.000  -0.0957   0.01737   0.00908  -0.0202   1.0000   1.0000
  -1.750  -0.0963   0.01768   0.00915  -0.0168   1.0000   1.0000
  -1.500  -0.0936   0.01802   0.00927  -0.0140   1.0000   1.0000
  -1.250  -0.0886   0.01838   0.00943  -0.0116   1.0000   1.0000
  -1.000  -0.0816   0.01878   0.00963  -0.0095   1.0000   1.0000
  -0.750  -0.0730   0.01921   0.00987  -0.0077   1.0000   1.0000
  -0.500  -0.0397   0.01984   0.01028  -0.0106   0.9922   1.0000
  -0.250   0.0193   0.02064   0.01082  -0.0180   0.9749   1.0000
   0.000   0.0784   0.02136   0.01136  -0.0253   0.9582   1.0000
   0.250   0.1307   0.02197   0.01182  -0.0310   0.9406   1.0000
   0.500   0.1812   0.02252   0.01228  -0.0361   0.9230   1.0000
   0.750   0.2349   0.02300   0.01271  -0.0416   0.9058   1.0000
   1.000   0.2871   0.02340   0.01308  -0.0465   0.8889   1.0000
   1.250   0.3341   0.02376   0.01344  -0.0502   0.8723   1.0000
   1.500   0.3750   0.02414   0.01383  -0.0524   0.8554   1.0000
   1.750   0.4012   0.02472   0.01442  -0.0523   0.8371   1.0000
   2.000   0.4294   0.02526   0.01497  -0.0522   0.8194   1.0000
   2.250   0.4575   0.02576   0.01552  -0.0519   0.8023   1.0000
   2.500   0.4846   0.02624   0.01603  -0.0513   0.7856   1.0000
   2.750   0.5106   0.02671   0.01654  -0.0503   0.7693   1.0000
   3.000   0.5303   0.02740   0.01727  -0.0487   0.7517   1.0000
   3.250   0.5497   0.02809   0.01805  -0.0470   0.7337   1.0000
   3.500   0.5711   0.02867   0.01869  -0.0453   0.7164   1.0000
   3.750   0.5934   0.02916   0.01924  -0.0435   0.6993   1.0000
   4.000   0.6165   0.02952   0.01968  -0.0416   0.6824   1.0000
   4.250   0.6372   0.03005   0.02032  -0.0396   0.6647   1.0000
   4.500   0.6551   0.03079   0.02116  -0.0376   0.6453   1.0000
   4.750   0.6771   0.03111   0.02158  -0.0354   0.6268   1.0000
   5.000   0.7016   0.03114   0.02169  -0.0330   0.6090   1.0000
   5.250   0.7195   0.03183   0.02254  -0.0310   0.5879   1.0000
   5.500   0.7427   0.03187   0.02269  -0.0285   0.5678   1.0000
   5.750   0.7648   0.03200   0.02292  -0.0261   0.5467   1.0000
   6.000   0.7878   0.03196   0.02298  -0.0235   0.5242   1.0000
   6.250   0.8090   0.03212   0.02329  -0.0211   0.5001   1.0000
   6.500   0.8341   0.03172   0.02293  -0.0183   0.4756   1.0000
   6.750   0.8591   0.03132   0.02253  -0.0156   0.4489   1.0000
   7.000   0.8807   0.03136   0.02262  -0.0132   0.4193   1.0000
   7.250   0.9003   0.03162   0.02297  -0.0107   0.3872   1.0000
   7.500   0.9209   0.03178   0.02310  -0.0082   0.3535   1.0000
   7.750   0.9418   0.03201   0.02317  -0.0058   0.3186   1.0000
   8.000   0.9578   0.03290   0.02404  -0.0034   0.2827   1.0000
   8.250   0.9745   0.03392   0.02485  -0.0010   0.2468   1.0000
   8.500   0.9874   0.03529   0.02610   0.0014   0.2109   1.0000
   8.750   0.9985   0.03687   0.02748   0.0036   0.1773   1.0000
   9.000   1.0092   0.03905   0.02955   0.0057   0.1500   1.0000
   9.250   1.0193   0.04173   0.03239   0.0077   0.1310   1.0000
   9.500   1.0315   0.04508   0.03596   0.0094   0.1198   1.0000
   9.750   1.0462   0.04832   0.03921   0.0106   0.1108   1.0000
  10.000   1.0447   0.05198   0.04347   0.0126   0.1064   1.0000
  10.250   1.0600   0.05512   0.04655   0.0136   0.0995   1.0000
  10.500   1.0569   0.05950   0.05129   0.0151   0.0983   1.0000
  10.750   1.0452   0.06382   0.05601   0.0167   0.0980   1.0000
  11.000   1.0302   0.06817   0.06065   0.0179   0.0980   1.0000
  11.250   1.0115   0.07246   0.06513   0.0191   0.0983   1.0000
  11.500   0.9922   0.07714   0.06994   0.0191   0.0987   1.0000
  11.750   0.9011   0.08913   0.08221   0.0095   0.1098   1.0000
  12.000   0.8805   0.09719   0.09025   0.0053   0.1112   1.0000
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