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EH 1.0/9.0 (eh1090-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EH 1.0/9.0 (eh1090-il)
Reynolds number: 50,000
Max Cl/Cd: 31.17 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eh1090-il-50000-n5.txt
Download as CSV file: xf-eh1090-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EH 1.0/9.0                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.6095   0.10373   0.09699  -0.0021   1.0000   0.0428
  -9.750  -0.6099   0.09862   0.09192  -0.0046   1.0000   0.0427
  -9.500  -0.6104   0.09355   0.08689  -0.0071   1.0000   0.0424
  -9.250  -0.6118   0.08840   0.08179  -0.0101   1.0000   0.0420
  -9.000  -0.6171   0.08298   0.07640  -0.0136   1.0000   0.0416
  -8.750  -0.6266   0.07796   0.07139  -0.0162   1.0000   0.0413
  -8.500  -0.6362   0.07350   0.06691  -0.0175   1.0000   0.0410
  -8.250  -0.6432   0.06892   0.06223  -0.0186   1.0000   0.0406
  -8.000  -0.6486   0.06425   0.05740  -0.0192   1.0000   0.0404
  -7.750  -0.6502   0.05975   0.05267  -0.0194   1.0000   0.0402
  -7.500  -0.6489   0.05528   0.04789  -0.0191   1.0000   0.0401
  -7.250  -0.6440   0.05098   0.04320  -0.0184   1.0000   0.0401
  -7.000  -0.6359   0.04683   0.03852  -0.0175   1.0000   0.0404
  -6.750  -0.6241   0.04297   0.03414  -0.0163   1.0000   0.0409
  -6.500  -0.6089   0.03936   0.02995  -0.0150   1.0000   0.0417
  -6.250  -0.5909   0.03625   0.02634  -0.0138   1.0000   0.0435
  -6.000  -0.5719   0.03425   0.02425  -0.0131   1.0000   0.0479
  -5.750  -0.5499   0.03195   0.02154  -0.0120   1.0000   0.0523
  -5.500  -0.5253   0.02953   0.01868  -0.0109   1.0000   0.0558
  -5.250  -0.5026   0.02779   0.01693  -0.0100   1.0000   0.0628
  -5.000  -0.4792   0.02624   0.01527  -0.0091   1.0000   0.0737
  -4.750  -0.4553   0.02464   0.01352  -0.0080   1.0000   0.0868
  -4.500  -0.4327   0.02333   0.01220  -0.0070   1.0000   0.1107
  -4.250  -0.4109   0.02200   0.01099  -0.0060   1.0000   0.1456
  -4.000  -0.3905   0.02065   0.00992  -0.0050   1.0000   0.1962
  -3.750  -0.3728   0.01930   0.00903  -0.0036   1.0000   0.2755
  -3.500  -0.3603   0.01785   0.00844  -0.0011   1.0000   0.4153
  -3.250  -0.3474   0.01682   0.00843   0.0031   1.0000   0.6179
  -3.000  -0.3216   0.01672   0.00853   0.0059   1.0000   0.7621
  -2.750  -0.2858   0.01692   0.00858   0.0065   1.0000   0.8477
  -2.500  -0.2335   0.01721   0.00852   0.0035   1.0000   0.9088
  -2.250  -0.1576   0.01736   0.00814  -0.0047   1.0000   0.9528
  -2.000  -0.0834   0.01710   0.00749  -0.0138   1.0000   0.9846
  -1.750  -0.0360   0.01673   0.00690  -0.0185   1.0000   1.0000
  -1.500  -0.0229   0.01657   0.00665  -0.0169   1.0000   1.0000
  -1.250  -0.0125   0.01647   0.00653  -0.0148   1.0000   1.0000
  -1.000  -0.0061   0.01646   0.00650  -0.0120   1.0000   1.0000
  -0.750  -0.0046   0.01655   0.00658  -0.0086   1.0000   1.0000
  -0.500   0.0390   0.01661   0.00656  -0.0128   0.9759   1.0000
  -0.250   0.0889   0.01665   0.00649  -0.0178   0.9503   1.0000
   0.000   0.1358   0.01664   0.00642  -0.0219   0.9235   1.0000
   0.250   0.1779   0.01663   0.00635  -0.0248   0.8956   1.0000
   0.500   0.2133   0.01666   0.00631  -0.0263   0.8670   1.0000
   0.750   0.2428   0.01672   0.00631  -0.0264   0.8389   1.0000
   1.000   0.2681   0.01682   0.00634  -0.0256   0.8120   1.0000
   1.250   0.2913   0.01695   0.00642  -0.0244   0.7867   1.0000
   1.500   0.3131   0.01711   0.00651  -0.0230   0.7621   1.0000
   1.750   0.3344   0.01729   0.00665  -0.0214   0.7382   1.0000
   2.000   0.3559   0.01749   0.00680  -0.0199   0.7160   1.0000
   2.250   0.3773   0.01771   0.00699  -0.0184   0.6940   1.0000
   2.500   0.3988   0.01795   0.00724  -0.0170   0.6726   1.0000
   2.750   0.4206   0.01820   0.00748  -0.0156   0.6518   1.0000
   3.000   0.4424   0.01847   0.00776  -0.0143   0.6312   1.0000
   3.250   0.4643   0.01876   0.00807  -0.0129   0.6109   1.0000
   3.500   0.4864   0.01906   0.00839  -0.0116   0.5913   1.0000
   3.750   0.5085   0.01938   0.00883  -0.0104   0.5708   1.0000
   4.000   0.5314   0.01970   0.00918  -0.0092   0.5515   1.0000
   4.250   0.5539   0.02007   0.00966  -0.0081   0.5302   1.0000
   4.500   0.5766   0.02042   0.01006  -0.0069   0.5104   1.0000
   4.750   0.5989   0.02082   0.01059  -0.0058   0.4886   1.0000
   5.000   0.6214   0.02121   0.01110  -0.0045   0.4677   1.0000
   5.250   0.6434   0.02163   0.01168  -0.0033   0.4446   1.0000
   5.500   0.6651   0.02206   0.01223  -0.0021   0.4206   1.0000
   5.750   0.6865   0.02249   0.01278  -0.0007   0.3953   1.0000
   6.000   0.7076   0.02296   0.01337   0.0006   0.3687   1.0000
   6.250   0.7278   0.02345   0.01408   0.0020   0.3382   1.0000
   6.500   0.7456   0.02392   0.01460   0.0037   0.2966   1.0000
   6.750   0.7606   0.02458   0.01514   0.0054   0.2386   1.0000
   7.000   0.7731   0.02587   0.01608   0.0069   0.1665   1.0000
   7.250   0.7832   0.02805   0.01780   0.0083   0.1049   1.0000
   7.500   0.7932   0.03037   0.01991   0.0100   0.0780   1.0000
   7.750   0.8042   0.03243   0.02192   0.0115   0.0630   1.0000
   8.000   0.8169   0.03439   0.02403   0.0132   0.0548   1.0000
   8.250   0.8284   0.03652   0.02617   0.0148   0.0503   1.0000
   8.500   0.8444   0.03859   0.02854   0.0163   0.0457   1.0000
   8.750   0.8573   0.04066   0.03087   0.0175   0.0411   1.0000
   9.000   0.8695   0.04328   0.03349   0.0187   0.0382   1.0000
   9.250   0.8838   0.04610   0.03674   0.0200   0.0368   1.0000
   9.500   0.8933   0.04924   0.04030   0.0212   0.0359   1.0000
   9.750   0.8972   0.05266   0.04412   0.0224   0.0352   1.0000
  10.000   0.8950   0.05628   0.04811   0.0234   0.0347   1.0000
  10.250   0.8864   0.05981   0.05191   0.0245   0.0346   1.0000
  10.500   0.8738   0.06373   0.05607   0.0245   0.0345   1.0000
  10.750   0.8583   0.06833   0.06088   0.0230   0.0346   1.0000
  11.000   0.8414   0.07366   0.06639   0.0201   0.0348   1.0000
  11.250   0.8230   0.07997   0.07284   0.0160   0.0351   1.0000
  11.500   0.8039   0.08730   0.08028   0.0109   0.0355   1.0000
  11.750   0.7869   0.09503   0.08807   0.0057   0.0360   1.0000
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