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E10(08%) (e228-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: E10(08%) (e228-il)
Reynolds number: 1,000,000
Max Cl/Cd: 75.6 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e228-il-1000000.txt
Download as CSV file: xf-e228-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.9630   0.08256   0.08059  -0.0007   1.0000   0.0049
 -14.000  -1.0187   0.06649   0.06423  -0.0114   1.0000   0.0047
 -13.750  -1.0558   0.05549   0.05298  -0.0191   1.0000   0.0047
 -13.500  -1.0683   0.04981   0.04715  -0.0228   1.0000   0.0047
 -13.250  -1.0752   0.04567   0.04290  -0.0252   1.0000   0.0048
 -13.000  -1.1045   0.03956   0.03651  -0.0269   1.0000   0.0047
 -12.750  -1.1152   0.03643   0.03322  -0.0264   1.0000   0.0047
 -12.500  -1.1182   0.03440   0.03109  -0.0251   1.0000   0.0048
 -12.250  -1.1263   0.03215   0.02867  -0.0226   1.0000   0.0048
 -12.000  -1.1241   0.03089   0.02731  -0.0202   1.0000   0.0049
 -11.750  -1.1201   0.02978   0.02611  -0.0175   1.0000   0.0050
 -11.500  -1.1150   0.02831   0.02449  -0.0151   1.0000   0.0051
 -11.250  -1.1026   0.02724   0.02331  -0.0136   1.0000   0.0053
 -11.000  -1.0905   0.02593   0.02186  -0.0120   1.0000   0.0054
 -10.750  -1.0751   0.02489   0.02070  -0.0106   1.0000   0.0057
 -10.500  -1.0599   0.02365   0.01932  -0.0092   1.0000   0.0059
 -10.250  -1.0430   0.02253   0.01807  -0.0080   1.0000   0.0061
 -10.000  -1.0251   0.02144   0.01684  -0.0068   1.0000   0.0063
  -9.750  -1.0043   0.02073   0.01603  -0.0059   1.0000   0.0064
  -9.500  -0.9918   0.01869   0.01378  -0.0040   1.0000   0.0068
  -9.250  -0.9743   0.01744   0.01240  -0.0027   1.0000   0.0073
  -9.000  -0.9519   0.01684   0.01177  -0.0020   1.0000   0.0076
  -8.750  -0.9295   0.01618   0.01105  -0.0013   1.0000   0.0079
  -8.500  -0.9066   0.01558   0.01039  -0.0006   1.0000   0.0084
  -8.250  -0.8831   0.01506   0.00981   0.0000   1.0000   0.0089
  -8.000  -0.8589   0.01460   0.00930   0.0005   1.0000   0.0094
  -7.750  -0.8363   0.01394   0.00856   0.0013   1.0000   0.0099
  -7.500  -0.8165   0.01289   0.00741   0.0026   1.0000   0.0110
  -7.250  -0.7922   0.01250   0.00700   0.0031   1.0000   0.0120
  -7.000  -0.7676   0.01218   0.00667   0.0036   1.0000   0.0130
  -6.750  -0.7436   0.01185   0.00631   0.0043   1.0000   0.0138
  -6.500  -0.7226   0.01136   0.00576   0.0055   1.0000   0.0145
  -6.250  -0.6939   0.01066   0.00498   0.0051   0.9958   0.0164
  -6.000  -0.6602   0.01027   0.00457   0.0036   0.9898   0.0183
  -5.750  -0.6257   0.00996   0.00422   0.0021   0.9838   0.0198
  -5.500  -0.5942   0.00955   0.00376   0.0013   0.9748   0.0230
  -5.250  -0.5655   0.00918   0.00341   0.0011   0.9640   0.0306
  -5.000  -0.5420   0.00867   0.00305   0.0019   0.9510   0.0628
  -4.750  -0.5194   0.00828   0.00279   0.0030   0.9383   0.0940
  -4.500  -0.4960   0.00798   0.00258   0.0039   0.9263   0.1220
  -4.250  -0.4721   0.00769   0.00237   0.0048   0.9145   0.1534
  -4.000  -0.4473   0.00741   0.00219   0.0054   0.9026   0.1847
  -3.750  -0.4225   0.00713   0.00201   0.0060   0.8910   0.2208
  -3.500  -0.3972   0.00687   0.00185   0.0066   0.8793   0.2572
  -3.250  -0.3715   0.00667   0.00172   0.0070   0.8675   0.2884
  -3.000  -0.3459   0.00645   0.00158   0.0075   0.8554   0.3264
  -2.750  -0.3205   0.00618   0.00146   0.0080   0.8429   0.3769
  -2.500  -0.2942   0.00600   0.00136   0.0083   0.8301   0.4116
  -2.250  -0.2680   0.00582   0.00126   0.0087   0.8172   0.4500
  -2.000  -0.2417   0.00565   0.00118   0.0090   0.8041   0.4873
  -1.750  -0.2152   0.00552   0.00110   0.0094   0.7906   0.5221
  -1.500  -0.1886   0.00539   0.00104   0.0097   0.7768   0.5559
  -1.250  -0.1621   0.00528   0.00099   0.0101   0.7622   0.5890
  -1.000  -0.1355   0.00517   0.00094   0.0104   0.7472   0.6224
  -0.750  -0.1090   0.00508   0.00091   0.0108   0.7319   0.6552
  -0.500  -0.0826   0.00500   0.00088   0.0112   0.7161   0.6875
  -0.250  -0.0562   0.00493   0.00086   0.0116   0.6997   0.7199
   0.000  -0.0298   0.00487   0.00085   0.0120   0.6829   0.7507
   0.250  -0.0034   0.00482   0.00085   0.0124   0.6655   0.7808
   0.500   0.0229   0.00479   0.00086   0.0129   0.6474   0.8094
   0.750   0.0493   0.00478   0.00088   0.0134   0.6289   0.8364
   1.000   0.0757   0.00478   0.00091   0.0138   0.6099   0.8618
   1.250   0.1025   0.00480   0.00094   0.0143   0.5896   0.8854
   1.500   0.1297   0.00485   0.00100   0.0146   0.5690   0.9073
   1.750   0.1580   0.00493   0.00106   0.0146   0.5465   0.9268
   2.000   0.1884   0.00506   0.00114   0.0142   0.5228   0.9422
   2.250   0.2199   0.00522   0.00123   0.0135   0.4980   0.9541
   2.500   0.2534   0.00539   0.00133   0.0123   0.4712   0.9620
   2.750   0.2835   0.00558   0.00143   0.0119   0.4444   0.9705
   3.000   0.3195   0.00578   0.00153   0.0101   0.4160   0.9741
   3.250   0.3541   0.00600   0.00165   0.0086   0.3859   0.9783
   3.500   0.3856   0.00623   0.00178   0.0077   0.3560   0.9831
   3.750   0.4226   0.00645   0.00190   0.0056   0.3247   0.9850
   4.000   0.4585   0.00672   0.00204   0.0037   0.2884   0.9874
   4.250   0.4934   0.00701   0.00220   0.0020   0.2525   0.9903
   4.500   0.5268   0.00733   0.00237   0.0006   0.2169   0.9933
   4.750   0.5622   0.00764   0.00255  -0.0012   0.1845   0.9952
   5.000   0.5976   0.00798   0.00275  -0.0032   0.1500   0.9972
   5.250   0.6321   0.00837   0.00298  -0.0049   0.1155   0.9991
   5.500   0.6615   0.00875   0.00323  -0.0056   0.0885   1.0000
   5.750   0.6841   0.00905   0.00346  -0.0047   0.0718   1.0000
   6.000   0.7065   0.00939   0.00373  -0.0038   0.0567   1.0000
   6.250   0.7288   0.00975   0.00402  -0.0029   0.0433   1.0000
   6.500   0.7513   0.01007   0.00431  -0.0020   0.0344   1.0000
   6.750   0.7737   0.01042   0.00463  -0.0010   0.0266   1.0000
   7.000   0.7958   0.01082   0.00500  -0.0001   0.0194   1.0000
   7.250   0.8172   0.01132   0.00549   0.0010   0.0132   1.0000
   7.500   0.8385   0.01185   0.00604   0.0022   0.0104   1.0000
   7.750   0.8603   0.01228   0.00650   0.0033   0.0092   1.0000
   8.000   0.8804   0.01294   0.00722   0.0046   0.0080   1.0000
   8.250   0.9005   0.01357   0.00793   0.0059   0.0074   1.0000
   8.500   0.9217   0.01404   0.00845   0.0070   0.0070   1.0000
   8.750   0.9424   0.01457   0.00904   0.0081   0.0065   1.0000
   9.000   0.9622   0.01517   0.00972   0.0093   0.0063   1.0000
   9.250   0.9816   0.01582   0.01043   0.0106   0.0060   1.0000
   9.500   1.0003   0.01651   0.01120   0.0120   0.0058   1.0000
   9.750   1.0174   0.01736   0.01213   0.0135   0.0056   1.0000
  10.000   1.0321   0.01841   0.01328   0.0153   0.0054   1.0000
  10.250   1.0441   0.01972   0.01471   0.0174   0.0052   1.0000
  10.500   1.0507   0.02155   0.01673   0.0201   0.0051   1.0000
  10.750   1.0624   0.02278   0.01809   0.0220   0.0050   1.0000
  11.000   1.0718   0.02417   0.01962   0.0241   0.0050   1.0000
  11.250   1.0845   0.02508   0.02065   0.0258   0.0049   1.0000
  11.500   1.0924   0.02616   0.02184   0.0282   0.0048   1.0000
  11.750   1.0956   0.02725   0.02305   0.0311   0.0047   1.0000
  12.000   1.0912   0.02915   0.02510   0.0340   0.0047   1.0000
  12.250   1.0941   0.03062   0.02669   0.0357   0.0046   1.0000
  12.500   1.0951   0.03242   0.02861   0.0369   0.0044   1.0000
  12.750   1.0924   0.03479   0.03113   0.0377   0.0043   1.0000
  13.000   1.0922   0.03713   0.03358   0.0378   0.0042   1.0000
  13.250   1.0779   0.04144   0.03810   0.0371   0.0043   1.0000
  13.500   1.0698   0.04542   0.04223   0.0355   0.0043   1.0000
  13.750   1.0585   0.05025   0.04722   0.0331   0.0042   1.0000
  14.000   1.0470   0.05552   0.05263   0.0301   0.0042   1.0000
  14.250   1.0366   0.06097   0.05821   0.0267   0.0041   1.0000
  14.500   1.0114   0.06925   0.06668   0.0217   0.0042   1.0000
  14.750   0.9922   0.07693   0.07450   0.0170   0.0041   1.0000
  15.000   0.9686   0.08572   0.08342   0.0118   0.0042   1.0000
  15.250   0.9422   0.09554   0.09338   0.0062   0.0043   1.0000
  15.500   0.9154   0.10585   0.10380   0.0006   0.0045   1.0000
  15.750   0.8864   0.11735   0.11542  -0.0055   0.0043   1.0000
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