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EH 2.0/7.0 (eh2070-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EH 2.0/7.0 (eh2070-il)
Reynolds number: 1,000,000
Max Cl/Cd: 86.83 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eh2070-il-1000000-n5.txt
Download as CSV file: xf-eh2070-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EH 2.0/7.0                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.5688   0.08403   0.08260   0.0084   1.0000   0.0019
  -8.000  -0.5718   0.08082   0.07941   0.0062   1.0000   0.0020
  -7.750  -0.5759   0.07682   0.07542   0.0030   1.0000   0.0020
  -7.500  -0.5728   0.07250   0.07107  -0.0003   1.0000   0.0021
  -7.250  -0.5665   0.06836   0.06690  -0.0030   1.0000   0.0022
  -7.000  -0.5576   0.06433   0.06282  -0.0054   1.0000   0.0022
  -6.750  -0.5469   0.06021   0.05864  -0.0074   1.0000   0.0023
  -6.500  -0.5343   0.05596   0.05431  -0.0091   1.0000   0.0025
  -6.250  -0.5206   0.05133   0.04957  -0.0104   1.0000   0.0025
  -6.000  -0.4945   0.04576   0.04376  -0.0140   0.9421   0.0027
  -5.750  -0.4816   0.04129   0.03887  -0.0131   0.8594   0.0028
  -5.500  -0.4654   0.03704   0.03426  -0.0123   0.8116   0.0030
  -5.250  -0.4474   0.03213   0.02897  -0.0113   0.7792   0.0032
  -5.000  -0.4281   0.02690   0.02331  -0.0099   0.7533   0.0035
  -4.750  -0.4117   0.01833   0.01390  -0.0070   0.7344   0.0036
  -4.500  -0.3890   0.01512   0.01011  -0.0056   0.7121   0.0039
  -4.250  -0.3634   0.01403   0.00875  -0.0050   0.6903   0.0043
  -4.000  -0.3366   0.01383   0.00841  -0.0048   0.6702   0.0046
  -3.750  -0.3126   0.01166   0.00584  -0.0040   0.6539   0.0056
  -3.500  -0.2862   0.01118   0.00523  -0.0037   0.6366   0.0061
  -3.250  -0.2597   0.01075   0.00468  -0.0034   0.6208   0.0065
  -3.000  -0.2331   0.01037   0.00419  -0.0031   0.6056   0.0070
  -2.750  -0.2070   0.00974   0.00339  -0.0026   0.5911   0.0070
  -2.500  -0.1807   0.00923   0.00273  -0.0022   0.5772   0.0069
  -2.250  -0.1541   0.00887   0.00224  -0.0018   0.5636   0.0069
  -2.000  -0.1271   0.00859   0.00184  -0.0015   0.5508   0.0070
  -1.750  -0.1000   0.00841   0.00155  -0.0013   0.5384   0.0071
  -1.500  -0.0726   0.00827   0.00132  -0.0011   0.5265   0.0074
  -1.250  -0.0451   0.00816   0.00114  -0.0010   0.5147   0.0084
  -1.000  -0.0177   0.00807   0.00099  -0.0009   0.5036   0.0137
  -0.750   0.0095   0.00791   0.00089  -0.0007   0.4924   0.0397
  -0.500   0.0368   0.00782   0.00082  -0.0007   0.4814   0.0593
  -0.250   0.0640   0.00770   0.00077  -0.0006   0.4706   0.0953
   0.000   0.0888   0.00704   0.00072  -0.0004   0.4603   0.3088
   0.250   0.1040   0.00538   0.00064   0.0017   0.4516   0.8106
   0.500   0.1296   0.00530   0.00065   0.0023   0.4424   0.8573
   0.750   0.1545   0.00525   0.00068   0.0032   0.4329   0.8995
   1.000   0.1804   0.00526   0.00071   0.0037   0.4231   0.9238
   1.250   0.2072   0.00531   0.00075   0.0042   0.4125   0.9447
   1.500   0.2362   0.00539   0.00080   0.0041   0.4009   0.9670
   1.750   0.2693   0.00548   0.00084   0.0029   0.3899   0.9751
   2.000   0.2989   0.00556   0.00087   0.0025   0.3795   0.9804
   2.250   0.3303   0.00563   0.00091   0.0017   0.3706   0.9827
   2.500   0.3623   0.00571   0.00096   0.0007   0.3620   0.9846
   2.750   0.3941   0.00580   0.00102  -0.0002   0.3529   0.9865
   3.000   0.4256   0.00589   0.00108  -0.0011   0.3434   0.9885
   3.250   0.4565   0.00600   0.00115  -0.0019   0.3312   0.9908
   3.500   0.4869   0.00611   0.00124  -0.0026   0.3196   0.9931
   3.750   0.5180   0.00623   0.00136  -0.0034   0.3078   0.9948
   4.000   0.5495   0.00636   0.00147  -0.0044   0.2937   0.9965
   4.250   0.5800   0.00668   0.00162  -0.0053   0.2522   0.9983
   4.500   0.6097   0.00719   0.00186  -0.0062   0.1918   0.9999
   4.750   0.6315   0.00796   0.00226  -0.0055   0.1098   1.0000
   5.000   0.6527   0.00883   0.00277  -0.0046   0.0334   1.0000
   5.250   0.6759   0.00932   0.00319  -0.0039   0.0088   1.0000
   5.500   0.7004   0.00959   0.00350  -0.0034   0.0069   1.0000
   5.750   0.7245   0.00998   0.00393  -0.0027   0.0048   1.0000
   6.000   0.7485   0.01040   0.00444  -0.0021   0.0038   1.0000
   6.250   0.7730   0.01072   0.00480  -0.0016   0.0032   1.0000
   6.500   0.7974   0.01111   0.00523  -0.0011   0.0027   1.0000
   6.750   0.8217   0.01154   0.00571  -0.0006   0.0023   1.0000
   7.000   0.8457   0.01204   0.00628  -0.0001   0.0021   1.0000
   7.250   0.8692   0.01263   0.00698   0.0004   0.0020   1.0000
   7.500   0.8917   0.01343   0.00790   0.0011   0.0018   1.0000
   7.750   0.9106   0.01486   0.00952   0.0022   0.0015   1.0000
   8.000   0.9342   0.01537   0.01008   0.0026   0.0014   1.0000
   8.250   0.9575   0.01591   0.01069   0.0030   0.0013   1.0000
   8.500   0.9786   0.01684   0.01173   0.0038   0.0012   1.0000
   8.750   0.9983   0.01797   0.01300   0.0046   0.0011   1.0000
   9.000   1.0156   0.01951   0.01472   0.0058   0.0010   1.0000
   9.250   1.0310   0.02136   0.01679   0.0071   0.0009   1.0000
   9.500   1.0438   0.02369   0.01937   0.0087   0.0009   1.0000
   9.750   1.0532   0.02648   0.02246   0.0104   0.0009   1.0000
  10.000   1.0558   0.03020   0.02655   0.0125   0.0009   1.0000
  10.250   1.0520   0.03424   0.03094   0.0148   0.0009   1.0000
  10.500   1.0390   0.03822   0.03523   0.0177   0.0009   1.0000
  10.750   1.0226   0.04134   0.03854   0.0200   0.0009   1.0000
  11.000   1.0011   0.04601   0.04343   0.0197   0.0009   1.0000
  11.250   0.9913   0.04986   0.04741   0.0179   0.0009   1.0000
  11.500   0.9691   0.05647   0.05420   0.0141   0.0009   1.0000
  11.750   0.9524   0.06285   0.06073   0.0098   0.0009   1.0000
  12.000   0.9348   0.07000   0.06801   0.0048   0.0009   1.0000
  12.250   0.9224   0.07663   0.07473   0.0002   0.0009   1.0000
  12.500   0.9078   0.08418   0.08238  -0.0049   0.0009   1.0000
  12.750   0.8883   0.09363   0.09192  -0.0110   0.0009   1.0000
  13.000   0.8726   0.10287   0.10123  -0.0165   0.0009   1.0000
  13.250   0.8557   0.11352   0.11195  -0.0220   0.0010   1.0000
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