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Eiffel 428 (Bleriot) (eiffel428-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: Eiffel 428 (Bleriot) (eiffel428-il)
Reynolds number: 500,000
Max Cl/Cd: 70.18 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-eiffel428-il-500000.txt
Download as CSV file: xf-eiffel428-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2692   0.09577   0.09365  -0.0368   1.0000   0.0261
 -10.500  -0.2735   0.09210   0.09000  -0.0386   1.0000   0.0263
 -10.250  -0.2762   0.08826   0.08619  -0.0399   1.0000   0.0264
 -10.000  -0.2776   0.08457   0.08252  -0.0408   1.0000   0.0265
  -9.750  -0.2791   0.08094   0.07893  -0.0413   1.0000   0.0265
  -9.500  -0.2796   0.07474   0.07274  -0.0432   0.9973   0.0269
  -9.250  -0.2591   0.07188   0.06988  -0.0440   0.9823   0.0276
  -9.000  -0.2374   0.06768   0.06565  -0.0485   0.9597   0.0286
  -8.750  -0.3499   0.07620   0.07415  -0.0467   0.9860   0.0270
  -8.500  -0.3285   0.07389   0.07182  -0.0481   0.9696   0.0277
  -8.250  -0.2914   0.06937   0.06725  -0.0571   0.9460   0.0288
  -8.000  -0.2297   0.05869   0.05633  -0.0836   0.9204   0.0331
  -7.750  -0.1999   0.05089   0.04818  -0.0940   0.8876   0.0333
  -7.500  -0.1996   0.04366   0.04072  -0.0965   0.8614   0.0342
  -7.250  -0.1844   0.04298   0.03992  -0.0954   0.8298   0.0348
  -7.000  -0.1692   0.04158   0.03835  -0.0949   0.8036   0.0357
  -6.750  -0.1535   0.03932   0.03588  -0.0949   0.7801   0.0370
  -6.500  -0.1295   0.03668   0.03270  -0.0956   0.7634   0.0418
  -6.250  -0.1123   0.03433   0.02996  -0.0950   0.7478   0.0421
  -6.000  -0.1046   0.02759   0.02288  -0.0950   0.7383   0.0436
  -5.750  -0.0838   0.02609   0.02130  -0.0945   0.7256   0.0445
  -5.500  -0.0625   0.02481   0.01985  -0.0939   0.7106   0.0458
  -5.250  -0.0405   0.02353   0.01836  -0.0933   0.6962   0.0477
  -5.000  -0.0122   0.02477   0.01928  -0.0922   0.6800   0.0529
  -4.750   0.0052   0.02116   0.01515  -0.0912   0.6678   0.0543
  -4.500   0.0268   0.01916   0.01303  -0.0906   0.6505   0.0561
  -4.250   0.0503   0.01816   0.01188  -0.0900   0.6285   0.0575
  -4.000   0.0748   0.01596   0.00920  -0.0886   0.6108   0.0478
  -3.750   0.0992   0.01495   0.00791  -0.0877   0.5865   0.0475
  -3.500   0.1238   0.01399   0.00665  -0.0868   0.5606   0.0467
  -3.250   0.1485   0.01337   0.00581  -0.0860   0.5326   0.0468
  -3.000   0.1729   0.01294   0.00516  -0.0852   0.4981   0.0471
  -2.750   0.1965   0.01269   0.00466  -0.0844   0.4525   0.0477
  -2.500   0.2203   0.01249   0.00425  -0.0835   0.4126   0.0483
  -2.250   0.2444   0.01242   0.00399  -0.0828   0.3731   0.0500
  -2.000   0.2619   0.01306   0.00401  -0.0811   0.2127   0.0510
  -1.750   0.2871   0.01288   0.00375  -0.0805   0.1970   0.0520
  -1.500   0.3110   0.01292   0.00360  -0.0798   0.1405   0.0528
  -1.250   0.3359   0.01269   0.00330  -0.0791   0.1364   0.0539
  -1.000   0.3604   0.01237   0.00295  -0.0785   0.1325   0.0563
  -0.750   0.3860   0.01223   0.00280  -0.0780   0.1303   0.0594
  -0.500   0.4118   0.01216   0.00272  -0.0776   0.1289   0.0631
  -0.250   0.4377   0.01213   0.00267  -0.0771   0.1277   0.0659
   0.000   0.4632   0.01208   0.00261  -0.0766   0.1259   0.0727
   0.250   0.4887   0.01206   0.00263  -0.0762   0.1246   0.0867
   0.500   0.5068   0.01103   0.00281  -0.0748   0.1234   0.5176
   0.750   0.5828   0.01024   0.00310  -0.0858   0.1201   1.0000
   1.000   0.6070   0.01044   0.00326  -0.0851   0.1180   1.0000
   1.250   0.6311   0.01065   0.00343  -0.0843   0.1163   1.0000
   1.500   0.6553   0.01083   0.00358  -0.0836   0.1149   1.0000
   1.750   0.6797   0.01101   0.00373  -0.0830   0.1129   1.0000
   2.000   0.7037   0.01122   0.00393  -0.0823   0.1104   1.0000
   2.250   0.7268   0.01150   0.00418  -0.0815   0.1074   1.0000
   2.500   0.7483   0.01191   0.00457  -0.0804   0.1036   1.0000
   2.750   0.7750   0.01188   0.00454  -0.0802   0.1005   1.0000
   3.000   0.8004   0.01197   0.00459  -0.0798   0.0956   1.0000
   3.250   0.8261   0.01203   0.00460  -0.0794   0.0899   1.0000
   3.500   0.8513   0.01213   0.00454  -0.0790   0.0605   1.0000
   3.750   0.8734   0.01248   0.00488  -0.0780   0.0526   1.0000
   4.000   0.8947   0.01290   0.00533  -0.0768   0.0489   1.0000
   4.250   0.9163   0.01329   0.00576  -0.0757   0.0462   1.0000
   4.500   0.9382   0.01364   0.00615  -0.0747   0.0448   1.0000
   4.750   0.9592   0.01406   0.00662  -0.0735   0.0426   1.0000
   5.000   0.9788   0.01457   0.00717  -0.0721   0.0407   1.0000
   5.250   0.9950   0.01531   0.00793  -0.0702   0.0385   1.0000
   5.500   1.0079   0.01624   0.00891  -0.0677   0.0365   1.0000
   5.750   1.0280   0.01664   0.00937  -0.0665   0.0351   1.0000
   6.000   1.0452   0.01722   0.00998  -0.0648   0.0333   1.0000
   6.250   1.0614   0.01785   0.01065  -0.0629   0.0316   1.0000
   6.500   1.0743   0.01868   0.01148  -0.0606   0.0298   1.0000
   6.750   1.0777   0.02014   0.01295  -0.0568   0.0283   1.0000
   7.000   1.0949   0.02049   0.01338  -0.0551   0.0273   1.0000
   7.250   1.1089   0.02112   0.01406  -0.0530   0.0260   1.0000
   7.500   1.1224   0.02184   0.01482  -0.0509   0.0249   1.0000
   7.750   1.1368   0.02242   0.01542  -0.0491   0.0235   1.0000
   8.000   1.1481   0.02341   0.01642  -0.0470   0.0226   1.0000
   8.250   1.1605   0.02499   0.01802  -0.0451   0.0215   1.0000
   8.500   1.1758   0.02572   0.01884  -0.0435   0.0207   1.0000
   8.750   1.1917   0.02670   0.01989  -0.0421   0.0198   1.0000
   9.000   1.2075   0.02772   0.02096  -0.0408   0.0190   1.0000
   9.250   1.2206   0.02861   0.02191  -0.0393   0.0183   1.0000
   9.500   1.2302   0.02939   0.02274  -0.0377   0.0176   1.0000
   9.750   1.2503   0.03144   0.02483  -0.0370   0.0166   1.0000
  10.000   1.2625   0.03243   0.02596  -0.0354   0.0160   1.0000
  10.250   1.2811   0.03406   0.02773  -0.0345   0.0153   1.0000
  10.500   1.3011   0.03604   0.02986  -0.0337   0.0148   1.0000
  10.750   1.3148   0.03786   0.03183  -0.0325   0.0144   1.0000
  11.000   1.3254   0.03977   0.03388  -0.0311   0.0140   1.0000
  11.250   1.3268   0.04072   0.03490  -0.0291   0.0137   1.0000
  11.500   1.3318   0.04259   0.03690  -0.0275   0.0135   1.0000
  11.750   1.3340   0.04432   0.03873  -0.0260   0.0132   1.0000
  12.000   1.3339   0.04701   0.04156  -0.0246   0.0129   1.0000
  12.250   1.3250   0.05171   0.04660  -0.0227   0.0126   1.0000
  12.500   1.3191   0.05450   0.04960  -0.0213   0.0124   1.0000
  12.750   1.3066   0.05888   0.05429  -0.0199   0.0122   1.0000
  13.000   1.2932   0.06318   0.05881  -0.0191   0.0122   1.0000
  13.250   1.2759   0.06795   0.06382  -0.0187   0.0121   1.0000
  13.500   1.2566   0.07308   0.06917  -0.0189   0.0121   1.0000
  13.750   1.2373   0.07837   0.07465  -0.0197   0.0121   1.0000
  14.000   1.2174   0.08398   0.08043  -0.0211   0.0122   1.0000
  14.250   1.1954   0.09031   0.08695  -0.0232   0.0122   1.0000
  14.500   1.1745   0.09692   0.09370  -0.0260   0.0123   1.0000
  14.750   1.1556   0.10358   0.10048  -0.0291   0.0125   1.0000
  15.000   1.1315   0.11192   0.10900  -0.0336   0.0124   1.0000
  15.250   1.1206   0.11800   0.11512  -0.0363   0.0127   1.0000
  15.500   1.1022   0.12615   0.12342  -0.0413   0.0128   1.0000
  15.750   1.0841   0.13507   0.13247  -0.0470   0.0129   1.0000
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