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E392 (10.15%) (e392-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: E392 (10.15%) (e392-il)
Reynolds number: 500,000
Max Cl/Cd: 113.56 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e392-il-500000-n5.txt
Download as CSV file: xf-e392-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3351   0.08954   0.08732  -0.0387   1.0000   0.0079
  -8.750  -0.3349   0.08650   0.08431  -0.0394   1.0000   0.0077
  -8.500  -0.3277   0.08256   0.08039  -0.0424   0.9898   0.0074
  -8.250  -0.3140   0.07720   0.07504  -0.0488   0.9754   0.0071
  -8.000  -0.2949   0.07053   0.06835  -0.0583   0.9509   0.0068
  -7.500  -0.3331   0.02982   0.02652  -0.0957   0.8544   0.0055
  -7.250  -0.3224   0.02456   0.02055  -0.0969   0.8342   0.0056
  -7.000  -0.3039   0.02172   0.01722  -0.0971   0.8175   0.0057
  -6.750  -0.2819   0.01986   0.01501  -0.0971   0.8028   0.0059
  -6.500  -0.2583   0.01841   0.01324  -0.0970   0.7892   0.0061
  -6.250  -0.2338   0.01714   0.01166  -0.0969   0.7767   0.0063
  -6.000  -0.2085   0.01604   0.01028  -0.0968   0.7652   0.0066
  -5.500  -0.1567   0.01423   0.00800  -0.0965   0.7437   0.0071
  -5.250  -0.1301   0.01357   0.00717  -0.0964   0.7342   0.0075
  -4.750  -0.0763   0.01253   0.00584  -0.0962   0.7161   0.0083
  -4.500  -0.0497   0.01176   0.00491  -0.0961   0.7081   0.0086
  -4.250  -0.0224   0.01124   0.00429  -0.0961   0.7000   0.0091
  -4.000   0.0051   0.01086   0.00382  -0.0961   0.6927   0.0096
  -3.750   0.0328   0.01054   0.00341  -0.0961   0.6852   0.0104
  -3.500   0.0606   0.01028   0.00304  -0.0960   0.6786   0.0112
  -3.250   0.0886   0.01003   0.00271  -0.0961   0.6717   0.0125
  -3.000   0.1164   0.00982   0.00244  -0.0961   0.6654   0.0163
  -2.750   0.1445   0.00951   0.00220  -0.0962   0.6592   0.0333
  -2.500   0.1724   0.00932   0.00203  -0.0962   0.6531   0.0542
  -2.250   0.2004   0.00911   0.00189  -0.0964   0.6473   0.0842
  -2.000   0.2283   0.00885   0.00178  -0.0966   0.6414   0.1361
  -1.750   0.2560   0.00857   0.00168  -0.0968   0.6363   0.2057
  -1.500   0.2841   0.00835   0.00161  -0.0970   0.6306   0.2632
  -1.250   0.3119   0.00814   0.00155  -0.0971   0.6250   0.3326
  -1.000   0.3397   0.00791   0.00153  -0.0973   0.6201   0.4152
  -0.750   0.3677   0.00775   0.00153  -0.0974   0.6147   0.4831
  -0.500   0.3954   0.00765   0.00153  -0.0974   0.6094   0.5356
  -0.250   0.4233   0.00756   0.00155  -0.0974   0.6045   0.5826
   0.000   0.4510   0.00748   0.00157  -0.0974   0.5992   0.6295
   0.250   0.4783   0.00742   0.00160  -0.0973   0.5942   0.6756
   0.500   0.5055   0.00734   0.00164  -0.0971   0.5892   0.7238
   0.750   0.5319   0.00725   0.00169  -0.0967   0.5839   0.7757
   1.000   0.5566   0.00717   0.00175  -0.0958   0.5791   0.8335
   1.250   0.5789   0.00705   0.00178  -0.0943   0.5740   0.9009
   1.500   0.6117   0.00698   0.00176  -0.0952   0.5685   1.0000
   1.750   0.6397   0.00707   0.00180  -0.0953   0.5634   1.0000
   2.000   0.6679   0.00714   0.00186  -0.0954   0.5576   1.0000
   2.250   0.6958   0.00724   0.00192  -0.0955   0.5515   1.0000
   2.500   0.7238   0.00733   0.00199  -0.0955   0.5446   1.0000
   2.750   0.7513   0.00744   0.00206  -0.0955   0.5365   1.0000
   3.000   0.7791   0.00753   0.00215  -0.0955   0.5281   1.0000
   3.250   0.8065   0.00766   0.00224  -0.0955   0.5198   1.0000
   3.500   0.8341   0.00776   0.00235  -0.0955   0.5104   1.0000
   3.750   0.8614   0.00789   0.00246  -0.0955   0.5007   1.0000
   4.000   0.8885   0.00803   0.00258  -0.0954   0.4899   1.0000
   4.500   0.9422   0.00835   0.00287  -0.0952   0.4651   1.0000
   4.750   0.9687   0.00853   0.00303  -0.0950   0.4506   1.0000
   5.000   0.9945   0.00878   0.00321  -0.0947   0.4278   1.0000
   5.250   1.0184   0.00918   0.00346  -0.0942   0.3899   1.0000
   5.500   1.0399   0.00982   0.00383  -0.0934   0.3327   1.0000
   5.750   1.0610   0.01053   0.00427  -0.0925   0.2797   1.0000
   6.500   1.1205   0.01297   0.00595  -0.0896   0.1311   1.0000
   6.750   1.1415   0.01362   0.00647  -0.0887   0.1037   1.0000
   7.000   1.1615   0.01433   0.00704  -0.0877   0.0767   1.0000
   7.250   1.1812   0.01504   0.00762  -0.0867   0.0540   1.0000
   7.500   1.2003   0.01577   0.00827  -0.0855   0.0349   1.0000
   7.750   1.2179   0.01658   0.00899  -0.0842   0.0183   1.0000
   8.000   1.2367   0.01726   0.00965  -0.0830   0.0137   1.0000
   8.250   1.2565   0.01782   0.01026  -0.0819   0.0124   1.0000
   8.500   1.2752   0.01843   0.01093  -0.0806   0.0115   1.0000
   8.750   1.2924   0.01910   0.01168  -0.0792   0.0107   1.0000
   9.000   1.3079   0.01984   0.01249  -0.0775   0.0102   1.0000
   9.250   1.3195   0.02065   0.01339  -0.0752   0.0098   1.0000
   9.500   1.3315   0.02140   0.01422  -0.0730   0.0096   1.0000
   9.750   1.3425   0.02224   0.01514  -0.0707   0.0094   1.0000
  10.000   1.3522   0.02318   0.01617  -0.0685   0.0092   1.0000
  10.250   1.3611   0.02422   0.01730  -0.0664   0.0090   1.0000
  10.500   1.3696   0.02535   0.01853  -0.0644   0.0086   1.0000
  10.750   1.3768   0.02663   0.01991  -0.0625   0.0084   1.0000
  11.000   1.3841   0.02799   0.02135  -0.0608   0.0081   1.0000
  11.250   1.3903   0.02952   0.02297  -0.0592   0.0079   1.0000
  11.500   1.3951   0.03126   0.02481  -0.0578   0.0077   1.0000
  11.750   1.3996   0.03311   0.02675  -0.0565   0.0075   1.0000
  12.000   1.4033   0.03514   0.02888  -0.0554   0.0074   1.0000
  12.250   1.4056   0.03738   0.03122  -0.0543   0.0072   1.0000
  12.500   1.4069   0.03982   0.03376  -0.0535   0.0071   1.0000
  12.750   1.4057   0.04262   0.03668  -0.0527   0.0069   1.0000
  13.000   1.4038   0.04559   0.03977  -0.0520   0.0068   1.0000
  13.250   1.3996   0.04893   0.04323  -0.0514   0.0067   1.0000
  13.500   1.4023   0.05154   0.04596  -0.0512   0.0066   1.0000
  13.750   1.4055   0.05417   0.04871  -0.0511   0.0065   1.0000
  14.000   1.4081   0.05692   0.05159  -0.0512   0.0064   1.0000
  14.250   1.4080   0.06009   0.05489  -0.0513   0.0063   1.0000
  14.500   1.4098   0.06313   0.05806  -0.0517   0.0061   1.0000
  14.750   1.4093   0.06656   0.06163  -0.0522   0.0059   1.0000
  15.000   1.4077   0.07024   0.06545  -0.0529   0.0058   1.0000
  15.250   1.4051   0.07420   0.06955  -0.0537   0.0057   1.0000
  15.500   1.4022   0.07833   0.07382  -0.0548   0.0056   1.0000
  15.750   1.3979   0.08279   0.07842  -0.0561   0.0055   1.0000
  16.000   1.3932   0.08746   0.08324  -0.0577   0.0054   1.0000
  16.250   1.3876   0.09240   0.08835  -0.0595   0.0053   1.0000
  16.500   1.3817   0.09756   0.09365  -0.0616   0.0052   1.0000
  16.750   1.3750   0.10298   0.09921  -0.0640   0.0052   1.0000
  17.000   1.3680   0.10861   0.10498  -0.0666   0.0051   1.0000
  17.250   1.3600   0.11456   0.11107  -0.0695   0.0050   1.0000
  17.500   1.3520   0.12069   0.11733  -0.0727   0.0050   1.0000
  17.750   1.3434   0.12706   0.12384  -0.0761   0.0049   1.0000
  18.000   1.3348   0.13359   0.13050  -0.0798   0.0048   1.0000
  18.250   1.3258   0.14036   0.13740  -0.0838   0.0048   1.0000
  18.500   1.3165   0.14737   0.14453  -0.0880   0.0047   1.0000
  18.750   1.3069   0.15462   0.15191  -0.0925   0.0047   1.0000
  19.000   1.2968   0.16216   0.15958  -0.0973   0.0047   1.0000
  19.250   1.2857   0.17017   0.16772  -0.1025   0.0047   1.0000
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