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E392 (10.15%) (e392-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: E392 (10.15%) (e392-il)
Reynolds number: 500,000
Max Cl/Cd: 120.6 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e392-il-500000.txt
Download as CSV file: xf-e392-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E392  (10.15%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3250   0.08432   0.08223  -0.0397   1.0000   0.0181
  -8.000  -0.3283   0.08159   0.07955  -0.0397   1.0000   0.0184
  -7.750  -0.3335   0.07900   0.07702  -0.0395   0.9996   0.0186
  -7.500  -0.3145   0.07357   0.07159  -0.0474   0.9904   0.0193
  -7.250  -0.2920   0.06658   0.06459  -0.0592   0.9776   0.0204
  -7.000  -0.2203   0.03240   0.03017  -0.0874   0.9101   0.0220
  -6.750  -0.2170   0.02816   0.02576  -0.0889   0.8853   0.0225
  -6.500  -0.2066   0.02551   0.02296  -0.0895   0.8638   0.0230
  -6.250  -0.1943   0.02247   0.01972  -0.0905   0.8458   0.0236
  -6.000  -0.1792   0.01945   0.01647  -0.0916   0.8304   0.0245
  -5.750  -0.1622   0.01614   0.01284  -0.0927   0.8169   0.0262
  -5.500  -0.1436   0.01945   0.01453  -0.1002   0.8384   0.0156
  -5.250  -0.1198   0.01687   0.01151  -0.0999   0.8240   0.0151
  -5.000  -0.0942   0.01532   0.00960  -0.0995   0.8106   0.0153
  -4.750  -0.0679   0.01427   0.00829  -0.0991   0.7980   0.0156
  -4.500  -0.0414   0.01338   0.00717  -0.0988   0.7862   0.0164
  -4.250  -0.0152   0.01226   0.00589  -0.0985   0.7754   0.0167
  -4.000   0.0112   0.01141   0.00491  -0.0983   0.7654   0.0171
  -3.750   0.0383   0.01083   0.00423  -0.0981   0.7557   0.0180
  -3.500   0.0658   0.01040   0.00372  -0.0980   0.7466   0.0196
  -3.250   0.0935   0.01011   0.00330  -0.0979   0.7383   0.0216
  -3.000   0.1214   0.00965   0.00279  -0.0979   0.7297   0.0286
  -2.750   0.1490   0.00910   0.00240  -0.0980   0.7224   0.0799
  -2.500   0.1767   0.00881   0.00223  -0.0981   0.7145   0.1264
  -2.250   0.2043   0.00849   0.00211  -0.0983   0.7076   0.2012
  -2.000   0.2316   0.00799   0.00202  -0.0986   0.7004   0.3309
  -1.750   0.2589   0.00769   0.00198  -0.0987   0.6942   0.4408
  -1.500   0.2865   0.00748   0.00196  -0.0987   0.6872   0.5190
  -1.250   0.3139   0.00737   0.00195  -0.0986   0.6812   0.5817
  -1.000   0.3413   0.00723   0.00196  -0.0985   0.6749   0.6419
  -0.750   0.3682   0.00713   0.00197  -0.0982   0.6688   0.6998
  -0.500   0.3946   0.00704   0.00199  -0.0978   0.6631   0.7551
  -0.250   0.4199   0.00692   0.00202  -0.0970   0.6571   0.8126
   0.000   0.4424   0.00684   0.00204  -0.0955   0.6519   0.8760
   0.250   0.4674   0.00670   0.00200  -0.0944   0.6460   0.9547
   0.500   0.5029   0.00672   0.00196  -0.0961   0.6402   1.0000
   0.750   0.5313   0.00682   0.00198  -0.0963   0.6349   1.0000
   1.000   0.5596   0.00688   0.00200  -0.0964   0.6290   1.0000
   1.250   0.5878   0.00699   0.00203  -0.0965   0.6237   1.0000
   1.500   0.6160   0.00707   0.00208  -0.0966   0.6180   1.0000
   1.750   0.6442   0.00715   0.00214  -0.0967   0.6123   1.0000
   2.000   0.6722   0.00727   0.00219  -0.0968   0.6070   1.0000
   2.250   0.7002   0.00734   0.00226  -0.0968   0.6005   1.0000
   2.500   0.7280   0.00745   0.00232  -0.0969   0.5944   1.0000
   2.750   0.7559   0.00752   0.00241  -0.0969   0.5872   1.0000
   3.000   0.7835   0.00762   0.00247  -0.0969   0.5803   1.0000
   3.250   0.8112   0.00770   0.00257  -0.0969   0.5729   1.0000
   3.500   0.8387   0.00781   0.00266  -0.0968   0.5657   1.0000
   3.750   0.8662   0.00789   0.00276  -0.0968   0.5576   1.0000
   4.000   0.8934   0.00802   0.00285  -0.0967   0.5498   1.0000
   4.250   0.9208   0.00809   0.00297  -0.0966   0.5406   1.0000
   4.500   0.9479   0.00821   0.00311  -0.0965   0.5320   1.0000
   4.750   0.9748   0.00833   0.00323  -0.0964   0.5225   1.0000
   5.000   1.0018   0.00844   0.00338  -0.0963   0.5118   1.0000
   5.250   1.0283   0.00858   0.00352  -0.0961   0.4980   1.0000
   5.500   1.0538   0.00876   0.00366  -0.0957   0.4789   1.0000
   5.750   1.0794   0.00895   0.00384  -0.0954   0.4567   1.0000
   6.000   1.1041   0.00922   0.00405  -0.0949   0.4311   1.0000
   6.250   1.1275   0.00961   0.00433  -0.0942   0.3952   1.0000
   6.500   1.1488   0.01021   0.00471  -0.0933   0.3451   1.0000
   6.750   1.1666   0.01114   0.00529  -0.0920   0.2781   1.0000
   7.000   1.1844   0.01210   0.00595  -0.0907   0.2205   1.0000
   7.250   1.2016   0.01308   0.00665  -0.0894   0.1683   1.0000
   7.500   1.2190   0.01400   0.00734  -0.0880   0.1259   1.0000
   7.750   1.2348   0.01502   0.00811  -0.0865   0.0840   1.0000
   8.000   1.2456   0.01641   0.00916  -0.0842   0.0369   1.0000
   8.250   1.2600   0.01743   0.01010  -0.0822   0.0224   1.0000
   8.500   1.2763   0.01825   0.01095  -0.0806   0.0192   1.0000
   8.750   1.2907   0.01915   0.01194  -0.0786   0.0176   1.0000
   9.000   1.3050   0.01993   0.01281  -0.0767   0.0167   1.0000
   9.250   1.3157   0.02076   0.01373  -0.0741   0.0161   1.0000
   9.500   1.3249   0.02168   0.01473  -0.0715   0.0154   1.0000
   9.750   1.3329   0.02269   0.01582  -0.0690   0.0147   1.0000
  10.000   1.3377   0.02398   0.01717  -0.0662   0.0140   1.0000
  10.250   1.3387   0.02561   0.01891  -0.0634   0.0136   1.0000
  10.500   1.3351   0.02778   0.02119  -0.0604   0.0132   1.0000
  10.750   1.3365   0.02975   0.02329  -0.0583   0.0129   1.0000
  11.000   1.3437   0.03133   0.02497  -0.0568   0.0127   1.0000
  11.250   1.3488   0.03320   0.02695  -0.0553   0.0126   1.0000
  11.500   1.3548   0.03508   0.02893  -0.0540   0.0124   1.0000
  11.750   1.3604   0.03708   0.03105  -0.0527   0.0122   1.0000
  12.000   1.3664   0.03911   0.03319  -0.0516   0.0119   1.0000
  12.250   1.3724   0.04121   0.03540  -0.0506   0.0116   1.0000
  12.500   1.3785   0.04331   0.03760  -0.0498   0.0112   1.0000
  12.750   1.3838   0.04548   0.03986  -0.0491   0.0108   1.0000
  13.000   1.3883   0.04785   0.04234  -0.0485   0.0105   1.0000
  13.250   1.3920   0.05041   0.04503  -0.0479   0.0103   1.0000
  13.500   1.3950   0.05313   0.04785  -0.0474   0.0100   1.0000
  13.750   1.3972   0.05605   0.05090  -0.0469   0.0099   1.0000
  14.000   1.3978   0.05940   0.05439  -0.0464   0.0097   1.0000
  14.250   1.3960   0.06326   0.05843  -0.0461   0.0095   1.0000
  14.500   1.3901   0.06778   0.06316  -0.0460   0.0094   1.0000
  14.750   1.3814   0.07267   0.06828  -0.0465   0.0094   1.0000
  15.000   1.3698   0.07801   0.07384  -0.0475   0.0094   1.0000
  15.250   1.3567   0.08366   0.07970  -0.0490   0.0093   1.0000
  15.500   1.3415   0.08987   0.08612  -0.0511   0.0093   1.0000
  15.750   1.3253   0.09645   0.09291  -0.0537   0.0093   1.0000
  16.000   1.3093   0.10330   0.09996  -0.0569   0.0093   1.0000
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