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Eiffel 428 (Bleriot) (eiffel428-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: Eiffel 428 (Bleriot) (eiffel428-il)
Reynolds number: 100,000
Max Cl/Cd: 50.49 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eiffel428-il-100000-n5.txt
Download as CSV file: xf-eiffel428-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2561   0.08955   0.08509  -0.0381   1.0000   0.0571
  -9.500  -0.2569   0.08654   0.08214  -0.0382   1.0000   0.0584
  -9.250  -0.3358   0.09343   0.08871  -0.0374   1.0000   0.0547
  -9.000  -0.3347   0.09083   0.08618  -0.0372   1.0000   0.0558
  -8.750  -0.3371   0.08836   0.08380  -0.0369   1.0000   0.0567
  -8.500  -0.3436   0.08617   0.08171  -0.0361   1.0000   0.0576
  -8.250  -0.3533   0.08418   0.07985  -0.0349   1.0000   0.0585
  -8.000  -0.2520   0.06466   0.06057  -0.0501   0.9600   0.0683
  -7.750  -0.2347   0.06019   0.05607  -0.0545   0.9485   0.0721
  -7.500  -0.2215   0.05397   0.04973  -0.0665   0.9335   0.0777
  -7.000  -0.2468   0.05475   0.04989  -0.0755   0.9363   0.0535
  -6.750  -0.2199   0.05142   0.04643  -0.0788   0.9248   0.0555
  -6.500  -0.1894   0.04716   0.04192  -0.0836   0.9123   0.0578
  -6.250  -0.1593   0.03950   0.03351  -0.0895   0.9012   0.0536
  -6.000  -0.1306   0.03548   0.02891  -0.0918   0.8868   0.0532
  -5.750  -0.1040   0.03380   0.02712  -0.0927   0.8696   0.0558
  -5.500  -0.0785   0.03153   0.02444  -0.0931   0.8523   0.0575
  -5.250  -0.0535   0.02908   0.02149  -0.0932   0.8372   0.0571
  -5.000  -0.0282   0.02707   0.01902  -0.0929   0.8228   0.0570
  -4.750  -0.0025   0.02542   0.01694  -0.0926   0.8095   0.0572
  -4.500   0.0235   0.02403   0.01515  -0.0922   0.7971   0.0578
  -4.250   0.0491   0.02293   0.01374  -0.0917   0.7853   0.0591
  -4.000   0.0753   0.02208   0.01259  -0.0912   0.7743   0.0616
  -3.750   0.1022   0.02123   0.01143  -0.0908   0.7638   0.0628
  -3.500   0.1287   0.02038   0.01034  -0.0903   0.7520   0.0631
  -3.250   0.1547   0.01965   0.00941  -0.0896   0.7390   0.0637
  -3.000   0.1809   0.01902   0.00861  -0.0890   0.7271   0.0644
  -2.750   0.2072   0.01834   0.00782  -0.0885   0.7176   0.0652
  -2.500   0.2324   0.01764   0.00713  -0.0880   0.7082   0.0667
  -2.250   0.2577   0.01714   0.00662  -0.0874   0.6991   0.0687
  -2.000   0.2831   0.01677   0.00622  -0.0868   0.6901   0.0720
  -1.750   0.3084   0.01649   0.00590  -0.0862   0.6809   0.0768
  -1.500   0.3338   0.01620   0.00553  -0.0856   0.6721   0.0804
  -1.250   0.3591   0.01591   0.00523  -0.0850   0.6618   0.0847
  -1.000   0.3850   0.01572   0.00497  -0.0845   0.6522   0.0904
  -0.750   0.4113   0.01550   0.00473  -0.0841   0.6425   0.1010
  -0.500   0.4375   0.01483   0.00467  -0.0840   0.6297   0.2721
   0.250   0.5446   0.01328   0.00450  -0.0887   0.5883   1.0000
   0.500   0.5694   0.01340   0.00450  -0.0881   0.5771   1.0000
   0.750   0.5943   0.01354   0.00453  -0.0874   0.5662   1.0000
   1.000   0.6193   0.01368   0.00462  -0.0868   0.5565   1.0000
   1.250   0.6442   0.01382   0.00471  -0.0862   0.5470   1.0000
   1.500   0.6692   0.01398   0.00482  -0.0857   0.5378   1.0000
   1.750   0.6935   0.01415   0.00493  -0.0849   0.5238   1.0000
   2.000   0.7166   0.01436   0.00503  -0.0840   0.5007   1.0000
   2.250   0.7382   0.01465   0.00512  -0.0828   0.4676   1.0000
   2.500   0.7589   0.01503   0.00527  -0.0814   0.4309   1.0000
   2.750   0.7792   0.01548   0.00552  -0.0801   0.3881   1.0000
   3.000   0.7872   0.01693   0.00607  -0.0772   0.2411   1.0000
   3.250   0.8062   0.01763   0.00659  -0.0759   0.2100   1.0000
   3.500   0.8282   0.01805   0.00699  -0.0750   0.1916   1.0000
   3.750   0.8476   0.01868   0.00751  -0.0738   0.1483   1.0000
   4.000   0.8670   0.01930   0.00801  -0.0726   0.1384   1.0000
   4.250   0.8855   0.01996   0.00859  -0.0713   0.1306   1.0000
   4.500   0.9046   0.02055   0.00919  -0.0700   0.1241   1.0000
   4.750   0.9220   0.02125   0.00993  -0.0685   0.1176   1.0000
   5.000   0.9416   0.02175   0.01052  -0.0674   0.1133   1.0000
   5.250   0.9612   0.02224   0.01112  -0.0662   0.1089   1.0000
   5.500   0.9787   0.02288   0.01183  -0.0647   0.1049   1.0000
   5.750   1.0002   0.02320   0.01235  -0.0637   0.0979   1.0000
   6.000   1.0242   0.02334   0.01270  -0.0630   0.0675   1.0000
   6.250   1.0356   0.02437   0.01347  -0.0608   0.0600   1.0000
   6.500   1.0461   0.02542   0.01452  -0.0584   0.0567   1.0000
   6.750   1.0545   0.02650   0.01568  -0.0557   0.0536   1.0000
   7.000   1.0604   0.02768   0.01698  -0.0527   0.0506   1.0000
   7.250   1.0641   0.02905   0.01844  -0.0496   0.0486   1.0000
   7.500   1.0642   0.03077   0.02024  -0.0465   0.0468   1.0000
   7.750   1.0732   0.03197   0.02160  -0.0444   0.0446   1.0000
   8.000   1.0802   0.03344   0.02316  -0.0423   0.0419   1.0000
   8.250   1.0870   0.03513   0.02488  -0.0403   0.0400   1.0000
   8.500   1.0998   0.03720   0.02678  -0.0387   0.0380   1.0000
   8.750   1.1142   0.03834   0.02812  -0.0374   0.0358   1.0000
   9.000   1.1311   0.03973   0.02961  -0.0363   0.0332   1.0000
   9.250   1.1545   0.04138   0.03133  -0.0357   0.0313   1.0000
   9.500   1.1899   0.04376   0.03363  -0.0366   0.0290   1.0000
   9.750   1.1971   0.04514   0.03535  -0.0346   0.0275   1.0000
  10.000   1.2133   0.04708   0.03754  -0.0335   0.0260   1.0000
  10.250   1.2298   0.04934   0.04004  -0.0326   0.0249   1.0000
  10.500   1.2427   0.05170   0.04261  -0.0315   0.0240   1.0000
  10.750   1.2527   0.05402   0.04509  -0.0304   0.0231   1.0000
  11.000   1.2635   0.05670   0.04792  -0.0296   0.0222   1.0000
  11.250   1.2634   0.05966   0.05112  -0.0280   0.0215   1.0000
  11.500   1.2535   0.06235   0.05417  -0.0259   0.0210   1.0000
  11.750   1.2454   0.06554   0.05769  -0.0244   0.0207   1.0000
  12.000   1.2359   0.06909   0.06154  -0.0233   0.0205   1.0000
  12.250   1.2239   0.07296   0.06570  -0.0226   0.0203   1.0000
  12.500   1.2102   0.07716   0.07017  -0.0224   0.0202   1.0000
  12.750   1.1945   0.08173   0.07501  -0.0227   0.0202   1.0000
  13.000   1.1778   0.08668   0.08020  -0.0236   0.0201   1.0000
  13.250   1.1600   0.09202   0.08576  -0.0251   0.0202   1.0000
  13.500   1.1410   0.09785   0.09182  -0.0272   0.0202   1.0000
  13.750   1.1215   0.10415   0.09832  -0.0300   0.0203   1.0000
  14.000   1.1013   0.11110   0.10546  -0.0335   0.0203   1.0000
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