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Eh 1.0/7.0 (eh1070-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: Eh 1.0/7.0 (eh1070-il)
Reynolds number: 50,000
Max Cl/Cd: 30.21 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-eh1070-il-50000.txt
Download as CSV file: xf-eh1070-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Eh 1.0/7.0                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.5864   0.09941   0.09310   0.0217   1.0000   0.2571
  -7.750  -0.5851   0.09601   0.08976   0.0216   1.0000   0.2722
  -7.500  -0.5901   0.09316   0.08702   0.0211   1.0000   0.2883
  -7.250  -0.5806   0.08904   0.08294   0.0223   1.0000   0.3070
  -7.000  -0.5830   0.08626   0.08025   0.0230   1.0000   0.3291
  -6.750  -0.5722   0.08249   0.07643   0.0249   1.0000   0.3550
  -6.500  -0.5745   0.07980   0.07383   0.0266   1.0000   0.3843
  -6.250  -0.5441   0.07559   0.06959   0.0314   1.0000   0.4338
  -5.500  -0.5473   0.05351   0.04642  -0.0115   1.0000   0.1813
  -5.250  -0.5182   0.04613   0.03826  -0.0135   1.0000   0.1245
  -5.000  -0.4955   0.04150   0.03305  -0.0132   1.0000   0.1100
  -4.750  -0.4732   0.03780   0.02887  -0.0126   1.0000   0.1073
  -4.500  -0.4497   0.03464   0.02511  -0.0118   1.0000   0.1085
  -4.250  -0.4243   0.03157   0.02150  -0.0108   1.0000   0.1084
  -4.000  -0.3970   0.02872   0.01816  -0.0098   1.0000   0.1089
  -3.750  -0.3684   0.02633   0.01523  -0.0086   1.0000   0.1131
  -3.500  -0.3418   0.02404   0.01301  -0.0078   1.0000   0.1317
  -3.250  -0.1932   0.01650   0.00856  -0.0188   1.0000   1.0000
  -3.000  -0.1742   0.01611   0.00768  -0.0181   1.0000   1.0000
  -2.750  -0.1549   0.01578   0.00697  -0.0173   1.0000   1.0000
  -2.500  -0.1355   0.01550   0.00638  -0.0164   1.0000   1.0000
  -2.250  -0.1159   0.01527   0.00587  -0.0155   1.0000   1.0000
  -2.000  -0.0963   0.01507   0.00544  -0.0145   1.0000   1.0000
  -1.750  -0.0769   0.01491   0.00502  -0.0134   1.0000   1.0000
  -1.500  -0.0576   0.01478   0.00472  -0.0123   1.0000   1.0000
  -1.250  -0.0388   0.01469   0.00449  -0.0111   1.0000   1.0000
  -1.000  -0.0204   0.01462   0.00431  -0.0098   1.0000   1.0000
  -0.750  -0.0028   0.01459   0.00420  -0.0084   1.0000   1.0000
  -0.500   0.0137   0.01459   0.00414  -0.0068   1.0000   1.0000
  -0.250   0.0287   0.01463   0.00411  -0.0050   1.0000   1.0000
   0.000   0.0422   0.01473   0.00418  -0.0030   1.0000   1.0000
   0.250   0.0540   0.01491   0.00432  -0.0010   1.0000   1.0000
   0.500   0.0642   0.01516   0.00456   0.0012   1.0000   1.0000
   0.750   0.0736   0.01552   0.00489   0.0031   1.0000   1.0000
   1.000   0.0829   0.01597   0.00531   0.0047   1.0000   1.0000
   1.250   0.0927   0.01652   0.00584   0.0059   1.0000   1.0000
   1.500   0.1031   0.01715   0.00647   0.0067   1.0000   1.0000
   1.750   0.1590   0.01811   0.00754  -0.0011   0.9802   1.0000
   2.000   0.2390   0.01890   0.00856  -0.0125   0.9470   1.0000
   2.250   0.3270   0.01927   0.00933  -0.0243   0.9150   1.0000
   2.500   0.3874   0.01948   0.00983  -0.0300   0.8803   1.0000
   2.750   0.4344   0.01964   0.01023  -0.0323   0.8473   1.0000
   3.000   0.4631   0.02001   0.01084  -0.0313   0.8137   1.0000
   3.250   0.4885   0.02037   0.01134  -0.0294   0.7820   1.0000
   3.500   0.5111   0.02074   0.01184  -0.0268   0.7517   1.0000
   3.750   0.5312   0.02124   0.01249  -0.0243   0.7199   1.0000
   4.000   0.5516   0.02172   0.01312  -0.0216   0.6887   1.0000
   4.250   0.5720   0.02214   0.01367  -0.0186   0.6575   1.0000
   4.500   0.5918   0.02263   0.01443  -0.0157   0.6228   1.0000
   4.750   0.6118   0.02291   0.01485  -0.0123   0.5866   1.0000
   5.000   0.6289   0.02262   0.01462  -0.0076   0.5356   1.0000
   5.250   0.6365   0.02107   0.01272  -0.0005   0.4364   1.0000
   5.500   0.6357   0.02331   0.01310   0.0051   0.1757   1.0000
   5.750   0.6540   0.02622   0.01550   0.0071   0.1229   1.0000
   6.000   0.6757   0.02857   0.01769   0.0086   0.1007   1.0000
   6.250   0.7015   0.03126   0.02039   0.0099   0.0917   1.0000
   6.500   0.7278   0.03434   0.02397   0.0112   0.0882   1.0000
   6.750   0.7510   0.03760   0.02779   0.0124   0.0857   1.0000
   7.000   0.7710   0.04083   0.03141   0.0134   0.0813   1.0000
   7.250   0.7895   0.04504   0.03569   0.0140   0.0781   1.0000
   7.500   0.8021   0.04888   0.04047   0.0152   0.0803   1.0000
   7.750   0.8071   0.05424   0.04659   0.0155   0.0843   1.0000
   8.000   0.8111   0.05954   0.05228   0.0155   0.0876   1.0000
   8.250   0.8241   0.06483   0.05764   0.0157   0.0911   1.0000
   8.500   0.7936   0.07133   0.06482   0.0122   0.0964   1.0000
   8.750   0.7849   0.07721   0.07078   0.0100   0.1008   1.0000
   9.000   0.7692   0.08331   0.07694   0.0065   0.1061   1.0000
   9.250   0.7414   0.09224   0.08577  -0.0026   0.1125   1.0000
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