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Eiffel 428 (Bleriot) (eiffel428-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: Eiffel 428 (Bleriot) (eiffel428-il)
Reynolds number: 50,000
Max Cl/Cd: 38.29 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-eiffel428-il-50000.txt
Download as CSV file: xf-eiffel428-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Eiffel 428 (Bleriot)                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3596   0.11204   0.10526  -0.0305   1.0000   0.1847
  -9.500  -0.3368   0.10611   0.09930  -0.0286   1.0000   0.1968
  -9.250  -0.3586   0.10685   0.10024  -0.0300   1.0000   0.2001
  -9.000  -0.3341   0.10088   0.09425  -0.0282   1.0000   0.2120
  -8.750  -0.3601   0.10173   0.09533  -0.0285   1.0000   0.2153
  -8.500  -0.3359   0.09612   0.08967  -0.0268   1.0000   0.2276
  -8.250  -0.3666   0.09705   0.09090  -0.0264   1.0000   0.2307
  -8.000  -0.3470   0.09217   0.08600  -0.0241   1.0000   0.2436
  -7.750  -0.3460   0.08935   0.08329  -0.0221   1.0000   0.2529
  -7.500  -0.3678   0.08914   0.08329  -0.0206   1.0000   0.2602
  -7.250  -0.3653   0.08624   0.08048  -0.0172   1.0000   0.2720
  -7.000  -0.3966   0.08683   0.08126  -0.0154   1.0000   0.2762
  -6.750  -0.3952   0.08403   0.07853  -0.0109   1.0000   0.2885
  -6.500  -0.4068   0.08239   0.07699  -0.0079   1.0000   0.2973
  -6.250  -0.4308   0.08263   0.07731  -0.0085   1.0000   0.3075
  -6.000  -0.4359   0.08060   0.07534  -0.0059   1.0000   0.3229
  -5.750  -0.4388   0.07820   0.07302  -0.0030   1.0000   0.3389
  -5.500  -0.4390   0.07553   0.07041   0.0009   1.0000   0.3560
  -5.250  -0.4386   0.07317   0.06810   0.0048   1.0000   0.3755
  -5.000  -0.4436   0.07131   0.06630   0.0071   1.0000   0.4027
  -4.750  -0.4461   0.06932   0.06434   0.0110   1.0000   0.4334
  -4.500  -0.4470   0.06708   0.06218   0.0169   1.0000   0.4672
  -3.750  -0.4571   0.06124   0.05659   0.0421   1.0000   0.6301
  -3.500  -0.4492   0.05874   0.05415   0.0499   1.0000   0.6920
  -3.250  -0.4367   0.05606   0.05150   0.0545   1.0000   0.7436
  -3.000  -0.1952   0.04239   0.03428  -0.0455   0.9911   0.1995
  -2.750  -0.1463   0.03979   0.03097  -0.0503   0.9831   0.1843
  -2.500  -0.1078   0.03776   0.02860  -0.0532   0.9746   0.1761
  -2.250  -0.0658   0.03635   0.02643  -0.0560   0.9664   0.1691
  -2.000  -0.0240   0.03531   0.02500  -0.0590   0.9579   0.1687
  -1.750   0.0092   0.03460   0.02411  -0.0607   0.9488   0.1734
  -1.500   0.0495   0.03406   0.02335  -0.0632   0.9386   0.1769
  -1.250   0.0997   0.03357   0.02251  -0.0669   0.9261   0.1826
  -1.000   0.1537   0.03312   0.02196  -0.0713   0.9130   0.1956
  -0.750   0.1928   0.03282   0.02169  -0.0734   0.8997   0.2191
  -0.500   0.2319   0.03236   0.02143  -0.0754   0.8869   0.2622
  -0.250   0.2903   0.03007   0.02083  -0.0803   0.8761   1.0000
   0.000   0.3296   0.03059   0.02095  -0.0822   0.8641   1.0000
   0.250   0.3752   0.03093   0.02099  -0.0850   0.8517   1.0000
   0.500   0.4053   0.03139   0.02127  -0.0855   0.8383   1.0000
   0.750   0.4318   0.03193   0.02167  -0.0854   0.8256   1.0000
   1.000   0.4586   0.03255   0.02219  -0.0856   0.8148   1.0000
   1.250   0.5013   0.03287   0.02243  -0.0880   0.8067   1.0000
   1.500   0.5093   0.03403   0.02353  -0.0857   0.7968   1.0000
   1.750   0.5512   0.03445   0.02394  -0.0881   0.7909   1.0000
   2.000   0.5538   0.03582   0.02527  -0.0852   0.7808   1.0000
   2.250   0.5872   0.03647   0.02593  -0.0864   0.7744   1.0000
   2.500   0.5939   0.03784   0.02729  -0.0843   0.7655   1.0000
   2.750   0.6211   0.03859   0.02807  -0.0845   0.7571   1.0000
   3.000   0.6487   0.03922   0.02877  -0.0846   0.7475   1.0000
   3.250   0.6626   0.04028   0.02987  -0.0831   0.7365   1.0000
   3.500   0.6970   0.04065   0.03032  -0.0837   0.7270   1.0000
   3.750   0.7235   0.04122   0.03102  -0.0834   0.7167   1.0000
   4.000   0.7369   0.04228   0.03216  -0.0818   0.7049   1.0000
   4.250   0.8176   0.03890   0.02904  -0.0841   0.6847   1.0000
   4.500   0.8519   0.03756   0.02787  -0.0821   0.6636   1.0000
   4.750   0.8894   0.03614   0.02663  -0.0807   0.6457   1.0000
   5.000   0.9205   0.03561   0.02630  -0.0797   0.6331   1.0000
   5.250   0.9519   0.03478   0.02570  -0.0782   0.6181   1.0000
   5.500   0.9960   0.03199   0.02309  -0.0763   0.5945   1.0000
   5.750   1.0248   0.03105   0.02234  -0.0745   0.5768   1.0000
   6.000   1.0422   0.03068   0.02224  -0.0716   0.5548   1.0000
   6.250   1.0643   0.02938   0.02113  -0.0681   0.5237   1.0000
   6.500   1.0780   0.02834   0.02014  -0.0635   0.4759   1.0000
   6.750   1.0813   0.02824   0.01989  -0.0581   0.3946   1.0000
   7.000   1.0669   0.02993   0.02033  -0.0515   0.2561   1.0000
   7.250   1.0499   0.03279   0.02254  -0.0463   0.2082   1.0000
   7.500   1.0431   0.03536   0.02485  -0.0428   0.1708   1.0000
   7.750   1.0397   0.03782   0.02698  -0.0400   0.1526   1.0000
   8.000   1.0423   0.04006   0.02902  -0.0376   0.1413   1.0000
   8.250   1.0642   0.04185   0.03046  -0.0355   0.1276   1.0000
   8.500   1.1786   0.04483   0.03344  -0.0422   0.1084   1.0000
   8.750   1.2235   0.04851   0.03731  -0.0440   0.1014   1.0000
   9.000   1.2479   0.05174   0.04101  -0.0432   0.0998   1.0000
   9.250   1.2656   0.05523   0.04494  -0.0419   0.0989   1.0000
   9.500   1.2753   0.05868   0.04883  -0.0399   0.0977   1.0000
   9.750   1.2798   0.06217   0.05271  -0.0377   0.0966   1.0000
  10.000   1.2790   0.06579   0.05672  -0.0352   0.0961   1.0000
  10.250   1.2715   0.06954   0.06087  -0.0324   0.0965   1.0000
  10.500   1.2557   0.07324   0.06493  -0.0292   0.0976   1.0000
  10.750   1.2359   0.07695   0.06891  -0.0261   0.0988   1.0000
  11.000   1.2148   0.08102   0.07322  -0.0239   0.0999   1.0000
  11.250   1.1939   0.08560   0.07800  -0.0229   0.1010   1.0000
  11.500   1.1774   0.09071   0.08327  -0.0227   0.1022   1.0000
  11.750   1.1717   0.09634   0.08903  -0.0229   0.1041   1.0000
  12.000   1.1126   0.10283   0.09576  -0.0260   0.1051   1.0000
  12.250   1.0364   0.11694   0.11000  -0.0357   0.1129   1.0000
  12.500   1.0336   0.12352   0.11658  -0.0375   0.1149   1.0000
  12.750   0.9956   0.13932   0.13231  -0.0474   0.1281   1.0000
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