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E230 (9.96%) (e230-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: E230 (9.96%) (e230-il)
Reynolds number: 500,000
Max Cl/Cd: 49.74 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e230-il-500000-n5.txt
Download as CSV file: xf-e230-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E230  (9.96%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.500  -0.9038   0.12856   0.12634   0.0473   1.0000   0.0054
 -14.250  -0.9449   0.11181   0.10947   0.0379   1.0000   0.0053
 -14.000  -0.9733   0.09949   0.09703   0.0305   1.0000   0.0052
 -13.750  -0.9983   0.08861   0.08601   0.0236   1.0000   0.0050
 -13.500  -1.0221   0.07839   0.07562   0.0166   1.0000   0.0051
 -13.250  -1.0422   0.06979   0.06685   0.0106   1.0000   0.0050
 -13.000  -1.0616   0.06218   0.05905   0.0055   1.0000   0.0050
 -12.750  -1.0785   0.05595   0.05263   0.0018   1.0000   0.0050
 -12.500  -1.0927   0.05097   0.04746  -0.0004   1.0000   0.0050
 -12.250  -1.1060   0.04675   0.04304  -0.0012   1.0000   0.0050
 -12.000  -1.1170   0.04332   0.03941  -0.0007   1.0000   0.0050
 -11.750  -1.1250   0.04055   0.03643   0.0007   1.0000   0.0051
 -11.500  -1.1316   0.03807   0.03375   0.0030   1.0000   0.0051
 -11.250  -1.1356   0.03589   0.03137   0.0058   1.0000   0.0052
 -11.000  -1.1361   0.03401   0.02929   0.0088   1.0000   0.0052
 -10.750  -1.1326   0.03231   0.02739   0.0115   1.0000   0.0053
 -10.500  -1.1242   0.03056   0.02543   0.0136   1.0000   0.0054
 -10.250  -1.1130   0.02895   0.02362   0.0154   1.0000   0.0054
 -10.000  -1.0989   0.02758   0.02207   0.0169   1.0000   0.0055
  -9.750  -1.0838   0.02618   0.02050   0.0184   1.0000   0.0056
  -9.500  -1.0668   0.02496   0.01913   0.0197   1.0000   0.0056
  -9.250  -1.0481   0.02393   0.01795   0.0208   1.0000   0.0057
  -9.000  -1.0322   0.02238   0.01626   0.0223   1.0000   0.0059
  -8.750  -1.0152   0.02100   0.01477   0.0236   1.0000   0.0062
  -8.500  -0.9958   0.01998   0.01368   0.0247   1.0000   0.0064
  -8.250  -0.9755   0.01904   0.01266   0.0257   1.0000   0.0066
  -8.000  -0.9545   0.01818   0.01172   0.0267   1.0000   0.0067
  -7.750  -0.9329   0.01736   0.01083   0.0276   1.0000   0.0069
  -7.500  -0.9108   0.01660   0.01000   0.0284   1.0000   0.0071
  -7.250  -0.8881   0.01590   0.00921   0.0291   1.0000   0.0073
  -7.000  -0.8648   0.01525   0.00849   0.0298   1.0000   0.0076
  -6.750  -0.8409   0.01466   0.00784   0.0304   1.0000   0.0078
  -6.500  -0.8165   0.01412   0.00724   0.0309   1.0000   0.0081
  -6.250  -0.7915   0.01365   0.00671   0.0314   1.0000   0.0084
  -6.000  -0.7667   0.01312   0.00611   0.0318   1.0000   0.0089
  -5.750  -0.7415   0.01266   0.00560   0.0322   1.0000   0.0096
  -5.500  -0.7097   0.01226   0.00516   0.0312   0.9675   0.0110
  -5.250  -0.6821   0.01193   0.00477   0.0313   0.9491   0.0129
  -5.000  -0.6592   0.01152   0.00438   0.0323   0.9326   0.0220
  -4.750  -0.6381   0.01100   0.00399   0.0337   0.9173   0.0514
  -4.500  -0.6160   0.01057   0.00368   0.0348   0.9034   0.0821
  -4.250  -0.5932   0.01018   0.00340   0.0358   0.8898   0.1127
  -4.000  -0.5698   0.00980   0.00313   0.0366   0.8766   0.1484
  -3.750  -0.5466   0.00938   0.00288   0.0375   0.8633   0.1935
  -3.500  -0.5226   0.00904   0.00267   0.0382   0.8502   0.2339
  -3.250  -0.4987   0.00867   0.00246   0.0390   0.8369   0.2824
  -3.000  -0.4744   0.00834   0.00228   0.0396   0.8234   0.3290
  -2.750  -0.4492   0.00812   0.00212   0.0402   0.8097   0.3618
  -2.500  -0.4236   0.00792   0.00198   0.0407   0.7959   0.3925
  -2.250  -0.3981   0.00773   0.00184   0.0412   0.7818   0.4252
  -2.000  -0.3724   0.00754   0.00172   0.0417   0.7673   0.4577
  -1.750  -0.3467   0.00738   0.00161   0.0422   0.7522   0.4891
  -1.500  -0.3209   0.00722   0.00151   0.0427   0.7368   0.5216
  -1.250  -0.2951   0.00707   0.00143   0.0432   0.7208   0.5538
  -1.000  -0.2694   0.00694   0.00136   0.0437   0.7041   0.5872
  -0.750  -0.2438   0.00680   0.00129   0.0442   0.6872   0.6211
  -0.500  -0.2182   0.00668   0.00124   0.0448   0.6699   0.6549
  -0.250  -0.1926   0.00658   0.00120   0.0454   0.6521   0.6885
   0.000  -0.1669   0.00649   0.00117   0.0460   0.6342   0.7207
   0.250  -0.1411   0.00641   0.00116   0.0466   0.6157   0.7521
   0.500  -0.1149   0.00635   0.00116   0.0471   0.5963   0.7825
   0.750  -0.0884   0.00632   0.00117   0.0475   0.5762   0.8115
   1.000  -0.0609   0.00632   0.00120   0.0478   0.5553   0.8390
   1.250  -0.0319   0.00635   0.00125   0.0477   0.5324   0.8643
   1.500  -0.0010   0.00642   0.00132   0.0472   0.5095   0.8870
   1.750   0.0335   0.00655   0.00142   0.0459   0.4842   0.9050
   2.000   0.0695   0.00671   0.00152   0.0442   0.4574   0.9190
   2.250   0.1055   0.00690   0.00164   0.0424   0.4294   0.9301
   2.500   0.1420   0.00712   0.00177   0.0406   0.3987   0.9376
   2.750   0.1741   0.00732   0.00190   0.0397   0.3712   0.9462
   3.000   0.2091   0.00755   0.00204   0.0381   0.3428   0.9512
   3.250   0.2368   0.00785   0.00220   0.0381   0.3041   0.9594
   3.500   0.2707   0.00829   0.00239   0.0365   0.2414   0.9630
   3.750   0.3025   0.00862   0.00258   0.0355   0.2049   0.9677
   4.000   0.3314   0.00896   0.00280   0.0350   0.1686   0.9731
   4.250   0.3655   0.00942   0.00305   0.0334   0.1226   0.9759
   4.500   0.3980   0.00981   0.00330   0.0321   0.0911   0.9794
   4.750   0.4278   0.01025   0.00361   0.0314   0.0609   0.9835
   5.000   0.4603   0.01073   0.00395   0.0301   0.0335   0.9858
   5.250   0.4937   0.01122   0.00435   0.0286   0.0166   0.9879
   5.500   0.5267   0.01157   0.00472   0.0273   0.0141   0.9902
   5.750   0.5589   0.01194   0.00514   0.0262   0.0127   0.9927
   6.000   0.5905   0.01239   0.00564   0.0251   0.0116   0.9949
   6.250   0.6235   0.01287   0.00618   0.0238   0.0111   0.9966
   6.500   0.6559   0.01331   0.00670   0.0225   0.0108   0.9983
   6.750   0.6879   0.01383   0.00731   0.0213   0.0103   0.9999
   7.000   0.7107   0.01437   0.00791   0.0220   0.0101   1.0000
   7.250   0.7325   0.01496   0.00857   0.0229   0.0098   1.0000
   7.500   0.7538   0.01560   0.00928   0.0238   0.0095   1.0000
   7.750   0.7745   0.01630   0.01005   0.0248   0.0093   1.0000
   8.000   0.7947   0.01704   0.01088   0.0258   0.0091   1.0000
   8.250   0.8144   0.01779   0.01169   0.0269   0.0088   1.0000
   8.500   0.8334   0.01861   0.01258   0.0280   0.0085   1.0000
   8.750   0.8509   0.01962   0.01366   0.0293   0.0082   1.0000
   9.000   0.8663   0.02094   0.01508   0.0308   0.0080   1.0000
   9.250   0.8807   0.02238   0.01666   0.0324   0.0079   1.0000
   9.500   0.8969   0.02341   0.01783   0.0338   0.0078   1.0000
   9.750   0.9123   0.02447   0.01903   0.0353   0.0077   1.0000
  10.000   0.9263   0.02564   0.02035   0.0369   0.0076   1.0000
  10.250   0.9384   0.02695   0.02182   0.0386   0.0075   1.0000
  10.500   0.9488   0.02832   0.02335   0.0404   0.0074   1.0000
  10.750   0.9559   0.02992   0.02513   0.0424   0.0074   1.0000
  11.000   0.9602   0.03158   0.02698   0.0445   0.0073   1.0000
  11.250   0.9601   0.03330   0.02888   0.0470   0.0072   1.0000
  11.500   0.9514   0.03509   0.03084   0.0501   0.0071   1.0000
  11.750   0.9439   0.03736   0.03326   0.0517   0.0071   1.0000
  12.000   0.9352   0.04029   0.03638   0.0520   0.0071   1.0000
  12.250   0.9248   0.04397   0.04024   0.0510   0.0071   1.0000
  12.500   0.9135   0.04835   0.04480   0.0487   0.0070   1.0000
  12.750   0.9018   0.05337   0.04999   0.0456   0.0070   1.0000
  13.000   0.8849   0.05987   0.05666   0.0411   0.0070   1.0000
  13.250   0.8666   0.06720   0.06415   0.0359   0.0071   1.0000
  13.500   0.8466   0.07533   0.07243   0.0304   0.0071   1.0000
  13.750   0.8198   0.08533   0.08255   0.0241   0.0071   1.0000
  14.000   0.7917   0.09587   0.09321   0.0181   0.0073   1.0000
  14.250   0.7439   0.11214   0.10961   0.0097   0.0074   1.0000
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