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E10(08%) (e228-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: E10(08%) (e228-il)
Reynolds number: 500,000
Max Cl/Cd: 66.19 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e228-il-500000.txt
Download as CSV file: xf-e228-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.7261   0.10502   0.10288   0.0093   1.0000   0.0150
 -12.000  -0.7234   0.10188   0.09975   0.0074   1.0000   0.0154
 -11.750  -0.8068   0.07266   0.07034  -0.0105   1.0000   0.0117
 -11.500  -0.7866   0.05199   0.04953  -0.0191   1.0000   0.0112
 -11.250  -0.9290   0.04724   0.04402  -0.0262   1.0000   0.0102
 -11.000  -0.9444   0.04414   0.04070  -0.0246   1.0000   0.0101
 -10.750  -0.9601   0.04121   0.03755  -0.0215   1.0000   0.0101
 -10.500  -0.9661   0.03863   0.03472  -0.0186   1.0000   0.0100
 -10.250  -0.9708   0.03511   0.03089  -0.0161   1.0000   0.0101
 -10.000  -0.9675   0.03215   0.02765  -0.0140   1.0000   0.0102
  -9.750  -0.9583   0.02977   0.02506  -0.0123   1.0000   0.0105
  -9.500  -0.9449   0.02794   0.02304  -0.0109   1.0000   0.0108
  -9.250  -0.9284   0.02656   0.02152  -0.0098   1.0000   0.0113
  -9.000  -0.9111   0.02503   0.01982  -0.0086   1.0000   0.0118
  -8.750  -0.8928   0.02346   0.01806  -0.0074   1.0000   0.0121
  -8.500  -0.8734   0.02202   0.01646  -0.0063   1.0000   0.0127
  -8.250  -0.8520   0.02103   0.01533  -0.0054   1.0000   0.0134
  -8.000  -0.8285   0.02055   0.01471  -0.0047   1.0000   0.0140
  -7.750  -0.8142   0.01786   0.01184  -0.0029   1.0000   0.0154
  -7.500  -0.7931   0.01692   0.01084  -0.0019   1.0000   0.0164
  -7.250  -0.7712   0.01611   0.00997  -0.0010   1.0000   0.0176
  -7.000  -0.7491   0.01535   0.00914  -0.0001   1.0000   0.0188
  -6.750  -0.7261   0.01478   0.00850   0.0008   1.0000   0.0198
  -6.500  -0.7080   0.01364   0.00726   0.0024   1.0000   0.0219
  -6.250  -0.6873   0.01300   0.00660   0.0036   1.0000   0.0240
  -6.000  -0.6670   0.01251   0.00605   0.0050   1.0000   0.0260
  -5.750  -0.6478   0.01214   0.00561   0.0067   1.0000   0.0278
  -5.500  -0.6327   0.01155   0.00500   0.0090   1.0000   0.0326
  -5.250  -0.6035   0.01093   0.00444   0.0085   0.9968   0.0465
  -5.000  -0.5693   0.01008   0.00391   0.0066   0.9915   0.1043
  -4.750  -0.5336   0.00954   0.00358   0.0045   0.9865   0.1521
  -4.500  -0.4964   0.00910   0.00330   0.0022   0.9824   0.1957
  -4.250  -0.4632   0.00871   0.00307   0.0009   0.9746   0.2381
  -4.000  -0.4302   0.00831   0.00286  -0.0004   0.9671   0.2876
  -3.750  -0.4007   0.00798   0.00268  -0.0008   0.9572   0.3345
  -3.500  -0.3757   0.00768   0.00254  -0.0002   0.9451   0.3827
  -3.250  -0.3521   0.00742   0.00242   0.0008   0.9326   0.4260
  -3.000  -0.3288   0.00721   0.00229   0.0019   0.9202   0.4631
  -2.750  -0.3056   0.00700   0.00218   0.0031   0.9079   0.5035
  -2.500  -0.2821   0.00681   0.00208   0.0042   0.8957   0.5428
  -2.250  -0.2581   0.00663   0.00199   0.0052   0.8834   0.5798
  -2.000  -0.2339   0.00647   0.00189   0.0062   0.8710   0.6157
  -1.750  -0.2093   0.00632   0.00182   0.0071   0.8579   0.6514
  -1.500  -0.1844   0.00618   0.00176   0.0079   0.8447   0.6861
  -1.250  -0.1593   0.00606   0.00171   0.0088   0.8313   0.7198
  -1.000  -0.1341   0.00596   0.00167   0.0096   0.8177   0.7525
  -0.750  -0.1087   0.00588   0.00164   0.0104   0.8037   0.7839
  -0.500  -0.0831   0.00581   0.00162   0.0112   0.7892   0.8136
  -0.250  -0.0571   0.00577   0.00162   0.0120   0.7743   0.8418
   0.000  -0.0306   0.00575   0.00162   0.0126   0.7589   0.8677
   0.250  -0.0029   0.00576   0.00164   0.0130   0.7430   0.8907
   0.500   0.0260   0.00581   0.00167   0.0131   0.7264   0.9113
   0.750   0.0571   0.00589   0.00172   0.0127   0.7087   0.9278
   1.000   0.0896   0.00600   0.00178   0.0120   0.6900   0.9412
   1.250   0.1251   0.00614   0.00185   0.0106   0.6705   0.9502
   1.500   0.1596   0.00628   0.00193   0.0094   0.6493   0.9589
   2.000   0.2327   0.00659   0.00208   0.0059   0.6026   0.9715
   2.250   0.2719   0.00674   0.00215   0.0035   0.5759   0.9760
   2.500   0.3061   0.00692   0.00225   0.0022   0.5490   0.9826
   2.750   0.3461   0.00707   0.00230  -0.0005   0.5186   0.9858
   3.000   0.3845   0.00724   0.00238  -0.0028   0.4868   0.9900
   3.250   0.4216   0.00744   0.00247  -0.0049   0.4542   0.9943
   3.500   0.4608   0.00761   0.00253  -0.0075   0.4183   0.9979
   3.750   0.4938   0.00782   0.00262  -0.0089   0.3828   1.0000
   4.000   0.5168   0.00801   0.00272  -0.0081   0.3508   1.0000
   4.250   0.5397   0.00825   0.00284  -0.0073   0.3173   1.0000
   4.500   0.5624   0.00853   0.00300  -0.0065   0.2828   1.0000
   4.750   0.5851   0.00884   0.00319  -0.0057   0.2475   1.0000
   5.000   0.6075   0.00920   0.00341  -0.0049   0.2131   1.0000
   5.250   0.6300   0.00956   0.00366  -0.0041   0.1813   1.0000
   5.500   0.6522   0.00997   0.00394  -0.0032   0.1494   1.0000
   5.750   0.6740   0.01043   0.00426  -0.0023   0.1192   1.0000
   6.000   0.6956   0.01093   0.00463  -0.0013   0.0916   1.0000
   6.250   0.7175   0.01137   0.00500  -0.0004   0.0717   1.0000
   6.500   0.7391   0.01185   0.00541   0.0006   0.0558   1.0000
   6.750   0.7605   0.01238   0.00588   0.0016   0.0425   1.0000
   7.000   0.7812   0.01299   0.00646   0.0028   0.0313   1.0000
   7.250   0.8013   0.01369   0.00714   0.0041   0.0223   1.0000
   7.500   0.8222   0.01426   0.00776   0.0052   0.0180   1.0000
   7.750   0.8401   0.01523   0.00881   0.0068   0.0153   1.0000
   8.000   0.8601   0.01589   0.00955   0.0081   0.0138   1.0000
   8.250   0.8792   0.01662   0.01034   0.0095   0.0126   1.0000
   8.500   0.8950   0.01772   0.01151   0.0113   0.0117   1.0000
   8.750   0.9050   0.01958   0.01352   0.0138   0.0111   1.0000
   9.000   0.9226   0.02049   0.01454   0.0153   0.0108   1.0000
   9.250   0.9400   0.02142   0.01561   0.0168   0.0104   1.0000
   9.500   0.9565   0.02243   0.01673   0.0183   0.0100   1.0000
   9.750   0.9722   0.02351   0.01792   0.0199   0.0095   1.0000
  10.000   0.9870   0.02463   0.01916   0.0214   0.0091   1.0000
  10.250   0.9989   0.02615   0.02084   0.0233   0.0089   1.0000
  10.500   1.0104   0.02752   0.02235   0.0250   0.0087   1.0000
  10.750   1.0195   0.02902   0.02399   0.0270   0.0085   1.0000
  11.000   1.0230   0.03102   0.02619   0.0294   0.0085   1.0000
  11.250   1.0231   0.03263   0.02794   0.0323   0.0084   1.0000
  11.500   1.0202   0.03460   0.03006   0.0348   0.0082   1.0000
  11.750   1.0164   0.03681   0.03242   0.0366   0.0081   1.0000
  12.000   1.0068   0.03993   0.03580   0.0378   0.0083   1.0000
  12.250   0.9992   0.04294   0.03895   0.0381   0.0081   1.0000
  12.500   0.9859   0.04698   0.04316   0.0375   0.0080   1.0000
  12.750   0.9714   0.05163   0.04800   0.0357   0.0079   1.0000
  13.000   0.9538   0.05723   0.05378   0.0329   0.0078   1.0000
  13.250   0.9438   0.06232   0.05907   0.0296   0.0080   1.0000
  13.500   0.9259   0.06925   0.06619   0.0250   0.0081   1.0000
  13.750   0.9036   0.07764   0.07477   0.0193   0.0082   1.0000
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