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E10(08%) (e228-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E10(08%) (e228-il)
Reynolds number: 100,000
Max Cl/Cd: 39.51 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e228-il-100000.txt
Download as CSV file: xf-e228-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E10(08%)                                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.6171   0.07640   0.07206  -0.0140   1.0000   0.0719
  -9.750  -0.7246   0.07574   0.07111  -0.0188   1.0000   0.0717
  -9.500  -0.7859   0.06637   0.06135  -0.0215   1.0000   0.0601
  -9.250  -0.7936   0.06161   0.05646  -0.0211   1.0000   0.0592
  -9.000  -0.8021   0.05704   0.05164  -0.0202   1.0000   0.0587
  -8.750  -0.8054   0.05239   0.04670  -0.0191   1.0000   0.0576
  -8.500  -0.8061   0.04793   0.04185  -0.0175   1.0000   0.0570
  -8.250  -0.8025   0.04366   0.03711  -0.0158   1.0000   0.0565
  -8.000  -0.7949   0.03947   0.03239  -0.0138   1.0000   0.0557
  -7.750  -0.7824   0.03584   0.02823  -0.0120   1.0000   0.0556
  -7.500  -0.7657   0.03278   0.02470  -0.0103   1.0000   0.0565
  -7.250  -0.7466   0.03068   0.02212  -0.0088   1.0000   0.0599
  -7.000  -0.7252   0.02797   0.01913  -0.0077   1.0000   0.0631
  -6.750  -0.7018   0.02586   0.01698  -0.0068   1.0000   0.0670
  -6.500  -0.6781   0.02424   0.01511  -0.0057   1.0000   0.0727
  -6.250  -0.6564   0.02253   0.01350  -0.0047   1.0000   0.0817
  -6.000  -0.6358   0.02088   0.01191  -0.0033   1.0000   0.0935
  -5.750  -0.6184   0.01926   0.01048  -0.0014   1.0000   0.1197
  -5.500  -0.6043   0.01766   0.00928   0.0009   1.0000   0.1823
  -5.250  -0.5893   0.01659   0.00860   0.0029   1.0000   0.2460
  -5.000  -0.5737   0.01593   0.00818   0.0049   1.0000   0.3100
  -4.750  -0.5585   0.01535   0.00782   0.0071   1.0000   0.3678
  -4.500  -0.5426   0.01480   0.00749   0.0094   1.0000   0.4189
  -4.250  -0.5265   0.01433   0.00719   0.0117   1.0000   0.4696
  -4.000  -0.5104   0.01391   0.00697   0.0141   1.0000   0.5190
  -3.750  -0.4943   0.01357   0.00678   0.0165   1.0000   0.5690
  -3.500  -0.4780   0.01328   0.00664   0.0191   1.0000   0.6171
  -3.250  -0.4615   0.01305   0.00656   0.0216   1.0000   0.6655
  -3.000  -0.4446   0.01290   0.00654   0.0242   1.0000   0.7132
  -2.750  -0.4266   0.01284   0.00659   0.0268   1.0000   0.7596
  -2.500  -0.4065   0.01288   0.00671   0.0290   1.0000   0.8062
  -2.250  -0.3810   0.01306   0.00689   0.0303   1.0000   0.8517
  -2.000  -0.3421   0.01342   0.00719   0.0290   1.0000   0.8929
  -1.750  -0.2891   0.01389   0.00753   0.0249   1.0000   0.9265
  -1.500  -0.2175   0.01434   0.00779   0.0169   1.0000   0.9476
  -1.250  -0.1482   0.01457   0.00788   0.0089   1.0000   0.9673
  -1.000  -0.0780   0.01458   0.00777   0.0002   1.0000   0.9845
  -0.750  -0.0043   0.01435   0.00745  -0.0094   1.0000   0.9997
  -0.500  -0.0339   0.01443   0.00752  -0.0027   1.0000   1.0000
  -0.250   0.0285   0.01447   0.00753  -0.0105   0.9862   1.0000
   0.000   0.0918   0.01444   0.00748  -0.0181   0.9727   1.0000
   0.250   0.1565   0.01431   0.00737  -0.0257   0.9596   1.0000
   0.500   0.2157   0.01408   0.00718  -0.0320   0.9437   1.0000
   0.750   0.2600   0.01389   0.00703  -0.0352   0.9219   1.0000
   1.000   0.2930   0.01373   0.00688  -0.0359   0.8989   1.0000
   1.250   0.3131   0.01367   0.00681  -0.0340   0.8732   1.0000
   1.500   0.3296   0.01363   0.00676  -0.0313   0.8480   1.0000
   1.750   0.3456   0.01360   0.00671  -0.0284   0.8240   1.0000
   2.000   0.3621   0.01357   0.00665  -0.0256   0.8007   1.0000
   2.250   0.3793   0.01358   0.00664  -0.0230   0.7759   1.0000
   2.500   0.3973   0.01360   0.00662  -0.0205   0.7517   1.0000
   2.750   0.4160   0.01361   0.00660  -0.0180   0.7276   1.0000
   3.000   0.4355   0.01367   0.00663  -0.0159   0.7007   1.0000
   3.250   0.4556   0.01374   0.00667  -0.0138   0.6730   1.0000
   3.500   0.4760   0.01384   0.00672  -0.0119   0.6442   1.0000
   3.750   0.4967   0.01397   0.00680  -0.0100   0.6142   1.0000
   4.000   0.5177   0.01414   0.00691  -0.0082   0.5822   1.0000
   4.250   0.5387   0.01435   0.00707  -0.0065   0.5476   1.0000
   4.500   0.5597   0.01460   0.00722  -0.0048   0.5127   1.0000
   4.750   0.5805   0.01490   0.00746  -0.0033   0.4734   1.0000
   5.000   0.6011   0.01527   0.00776  -0.0017   0.4323   1.0000
   5.250   0.6211   0.01572   0.00809  -0.0001   0.3884   1.0000
   5.500   0.6404   0.01629   0.00847   0.0014   0.3420   1.0000
   5.750   0.6592   0.01698   0.00900   0.0030   0.2918   1.0000
   6.000   0.6769   0.01787   0.00964   0.0046   0.2435   1.0000
   6.250   0.6940   0.01894   0.01048   0.0062   0.1993   1.0000
   6.500   0.7115   0.02011   0.01149   0.0078   0.1619   1.0000
   6.750   0.7288   0.02142   0.01263   0.0094   0.1330   1.0000
   7.000   0.7467   0.02283   0.01399   0.0110   0.1097   1.0000
   7.250   0.7646   0.02441   0.01542   0.0124   0.0919   1.0000
   7.500   0.7834   0.02636   0.01729   0.0137   0.0778   1.0000
   7.750   0.8020   0.02777   0.01886   0.0152   0.0667   1.0000
   8.000   0.8218   0.03024   0.02165   0.0167   0.0601   1.0000
   8.250   0.8398   0.03233   0.02371   0.0178   0.0536   1.0000
   8.500   0.8553   0.03516   0.02700   0.0195   0.0506   1.0000
   8.750   0.8680   0.03825   0.03059   0.0215   0.0490   1.0000
   9.000   0.8764   0.04172   0.03455   0.0235   0.0482   1.0000
   9.250   0.8796   0.04558   0.03888   0.0256   0.0481   1.0000
   9.500   0.8777   0.04960   0.04333   0.0276   0.0484   1.0000
   9.750   0.8700   0.05362   0.04772   0.0295   0.0483   1.0000
  10.000   0.8572   0.05759   0.05199   0.0312   0.0484   1.0000
  10.250   0.8377   0.06143   0.05604   0.0329   0.0489   1.0000
  10.500   0.8185   0.06570   0.06044   0.0332   0.0502   1.0000
  10.750   0.7974   0.07048   0.06534   0.0317   0.0507   1.0000
  11.000   0.7764   0.07627   0.07121   0.0285   0.0513   1.0000
  11.250   0.7646   0.08224   0.07720   0.0259   0.0523   1.0000
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