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EH 0.0/9.0 (eh0009-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EH 0.0/9.0 (eh0009-il)
Reynolds number: 100,000
Max Cl/Cd: 35.58 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eh0009-il-100000-n5.txt
Download as CSV file: xf-eh0009-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EH 0.0/9.0                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.7160   0.08465   0.07983  -0.0064   1.0000   0.0176
 -10.500  -0.7347   0.07534   0.07049  -0.0136   1.0000   0.0173
 -10.250  -0.7535   0.06806   0.06311  -0.0197   1.0000   0.0170
 -10.000  -0.7733   0.06236   0.05727  -0.0235   1.0000   0.0169
  -9.750  -0.7922   0.05798   0.05272  -0.0245   1.0000   0.0168
  -9.500  -0.8085   0.05430   0.04883  -0.0233   1.0000   0.0167
  -9.250  -0.8186   0.05034   0.04456  -0.0222   1.0000   0.0168
  -9.000  -0.8233   0.04635   0.04017  -0.0208   1.0000   0.0169
  -8.750  -0.8220   0.04264   0.03602  -0.0192   1.0000   0.0172
  -8.500  -0.8153   0.03928   0.03218  -0.0176   1.0000   0.0178
  -8.250  -0.8026   0.03697   0.02935  -0.0161   1.0000   0.0190
  -8.000  -0.7920   0.03356   0.02569  -0.0149   1.0000   0.0206
  -7.750  -0.7755   0.03147   0.02339  -0.0138   1.0000   0.0222
  -7.500  -0.7569   0.02924   0.02087  -0.0126   1.0000   0.0234
  -7.250  -0.7372   0.02721   0.01859  -0.0114   1.0000   0.0250
  -7.000  -0.7171   0.02542   0.01657  -0.0101   1.0000   0.0270
  -6.750  -0.6981   0.02382   0.01476  -0.0088   1.0000   0.0305
  -6.500  -0.6784   0.02263   0.01351  -0.0077   1.0000   0.0355
  -6.250  -0.6584   0.02141   0.01208  -0.0063   1.0000   0.0400
  -6.000  -0.6395   0.02019   0.01087  -0.0051   1.0000   0.0490
  -5.750  -0.6198   0.01907   0.00973  -0.0038   1.0000   0.0622
  -5.500  -0.6004   0.01795   0.00871  -0.0025   1.0000   0.0857
  -5.250  -0.5806   0.01694   0.00791  -0.0014   1.0000   0.1272
  -5.000  -0.5604   0.01609   0.00727  -0.0003   1.0000   0.1756
  -4.750  -0.5408   0.01528   0.00671   0.0008   1.0000   0.2416
  -4.500  -0.5207   0.01463   0.00628   0.0020   1.0000   0.3007
  -4.250  -0.5001   0.01410   0.00591   0.0032   1.0000   0.3537
  -4.000  -0.4794   0.01363   0.00559   0.0045   1.0000   0.4052
  -3.750  -0.4586   0.01323   0.00533   0.0059   1.0000   0.4545
  -3.500  -0.4376   0.01288   0.00510   0.0072   1.0000   0.5010
  -3.250  -0.4167   0.01258   0.00487   0.0087   1.0000   0.5450
  -3.000  -0.3957   0.01233   0.00473   0.0102   1.0000   0.5870
  -2.750  -0.3747   0.01212   0.00461   0.0117   1.0000   0.6268
  -2.500  -0.3537   0.01196   0.00453   0.0133   1.0000   0.6652
  -2.250  -0.3327   0.01184   0.00448   0.0148   1.0000   0.7014
  -2.000  -0.3115   0.01175   0.00443   0.0164   1.0000   0.7367
  -1.750  -0.2905   0.01171   0.00444   0.0180   1.0000   0.7702
  -1.500  -0.2665   0.01170   0.00447   0.0189   0.9982   0.8030
  -1.250  -0.2268   0.01177   0.00455   0.0167   0.9883   0.8339
  -1.000  -0.1850   0.01185   0.00461   0.0141   0.9791   0.8619
  -0.750  -0.1412   0.01193   0.00468   0.0111   0.9697   0.8864
  -0.500  -0.0952   0.01199   0.00473   0.0077   0.9599   0.9060
  -0.250  -0.0478   0.01203   0.00475   0.0039   0.9496   0.9233
   0.000   0.0000   0.01204   0.00476   0.0000   0.9376   0.9377
   0.250   0.0478   0.01203   0.00475  -0.0039   0.9233   0.9496
   0.500   0.0952   0.01199   0.00473  -0.0077   0.9061   0.9599
   0.750   0.1411   0.01193   0.00468  -0.0111   0.8864   0.9697
   1.000   0.1850   0.01185   0.00461  -0.0141   0.8619   0.9791
   1.250   0.2268   0.01177   0.00455  -0.0167   0.8340   0.9884
   1.500   0.2665   0.01170   0.00447  -0.0189   0.8030   0.9983
   1.750   0.2903   0.01171   0.00444  -0.0179   0.7701   1.0000
   2.000   0.3113   0.01175   0.00443  -0.0163   0.7367   1.0000
   2.250   0.3325   0.01184   0.00448  -0.0148   0.7016   1.0000
   2.500   0.3535   0.01196   0.00453  -0.0132   0.6651   1.0000
   2.750   0.3744   0.01212   0.00461  -0.0117   0.6270   1.0000
   3.000   0.3955   0.01233   0.00473  -0.0101   0.5870   1.0000
   3.250   0.4164   0.01258   0.00487  -0.0087   0.5452   1.0000
   3.500   0.4374   0.01288   0.00510  -0.0072   0.5011   1.0000
   3.750   0.4584   0.01322   0.00533  -0.0058   0.4547   1.0000
   4.000   0.4792   0.01363   0.00559  -0.0045   0.4056   1.0000
   4.250   0.4999   0.01409   0.00591  -0.0032   0.3539   1.0000
   4.500   0.5205   0.01463   0.00628  -0.0019   0.3006   1.0000
   4.750   0.5407   0.01528   0.00671  -0.0007   0.2418   1.0000
   5.000   0.5603   0.01609   0.00727   0.0004   0.1760   1.0000
   5.250   0.5805   0.01694   0.00791   0.0014   0.1271   1.0000
   5.500   0.6003   0.01794   0.00871   0.0025   0.0859   1.0000
   5.750   0.6198   0.01907   0.00972   0.0038   0.0622   1.0000
   6.000   0.6394   0.02019   0.01087   0.0051   0.0490   1.0000
   6.250   0.6584   0.02141   0.01208   0.0063   0.0400   1.0000
   6.500   0.6785   0.02263   0.01351   0.0077   0.0355   1.0000
   6.750   0.6981   0.02382   0.01476   0.0088   0.0304   1.0000
   7.000   0.7172   0.02543   0.01658   0.0100   0.0270   1.0000
   7.250   0.7373   0.02721   0.01859   0.0113   0.0250   1.0000
   7.500   0.7570   0.02923   0.02087   0.0126   0.0234   1.0000
   7.750   0.7756   0.03149   0.02340   0.0138   0.0221   1.0000
   8.000   0.7922   0.03357   0.02570   0.0149   0.0206   1.0000
   8.250   0.8030   0.03687   0.02927   0.0161   0.0189   1.0000
   8.500   0.8156   0.03929   0.03219   0.0176   0.0178   1.0000
   8.750   0.8223   0.04265   0.03604   0.0191   0.0172   1.0000
   9.000   0.8235   0.04642   0.04025   0.0207   0.0169   1.0000
   9.250   0.8192   0.05034   0.04456   0.0221   0.0168   1.0000
   9.500   0.8091   0.05433   0.04886   0.0232   0.0167   1.0000
   9.750   0.7924   0.05806   0.05280   0.0243   0.0167   1.0000
  10.000   0.7732   0.06251   0.05743   0.0232   0.0168   1.0000
  10.250   0.7549   0.06800   0.06305   0.0196   0.0171   1.0000
  10.500   0.7350   0.07555   0.07070   0.0133   0.0173   1.0000
  10.750   0.7165   0.08486   0.08004   0.0061   0.0176   1.0000
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