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Eiffel 428 (Bleriot) (eiffel428-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: Eiffel 428 (Bleriot) (eiffel428-il)
Reynolds number: 200,000
Max Cl/Cd: 67.72 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-eiffel428-il-200000.txt
Download as CSV file: xf-eiffel428-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3349   0.08844   0.08510  -0.0362   1.0000   0.0455
  -8.750  -0.3360   0.08601   0.08274  -0.0359   1.0000   0.0464
  -8.500  -0.3414   0.08383   0.08063  -0.0351   1.0000   0.0473
  -8.250  -0.3538   0.08219   0.07910  -0.0331   1.0000   0.0479
  -8.000  -0.3571   0.07967   0.07667  -0.0346   0.9970   0.0494
  -7.750  -0.3043   0.07059   0.06729  -0.0644   0.9777   0.0532
  -7.500  -0.2875   0.06399   0.06078  -0.0658   0.9710   0.0547
  -7.250  -0.2615   0.06074   0.05751  -0.0675   0.9589   0.0564
  -7.000  -0.2303   0.05662   0.05329  -0.0732   0.9471   0.0594
  -6.750  -0.1873   0.04815   0.04416  -0.0886   0.9325   0.0671
  -6.500  -0.1607   0.04522   0.04139  -0.0897   0.9222   0.0694
  -6.250  -0.1296   0.04244   0.03850  -0.0928   0.9097   0.0733
  -6.000  -0.1007   0.03762   0.03308  -0.0974   0.8940   0.0825
  -5.750  -0.0770   0.03563   0.03110  -0.0978   0.8785   0.0853
  -5.500  -0.0548   0.03326   0.02825  -0.0985   0.8627   0.0976
  -5.250  -0.0337   0.03164   0.02667  -0.0980   0.8476   0.1016
  -5.000  -0.0123   0.02970   0.02440  -0.0978   0.8348   0.1141
  -4.750   0.0092   0.02838   0.02282  -0.0973   0.8220   0.1282
  -4.500   0.0304   0.02724   0.02155  -0.0966   0.8083   0.1430
  -4.250   0.0517   0.02615   0.02041  -0.0958   0.7944   0.1585
  -3.750   0.1123   0.02011   0.01250  -0.0929   0.7751   0.0811
  -3.500   0.1367   0.01804   0.01027  -0.0922   0.7635   0.0771
  -3.250   0.1625   0.01694   0.00894  -0.0914   0.7528   0.0754
  -3.000   0.1884   0.01626   0.00804  -0.0907   0.7417   0.0765
  -2.750   0.2144   0.01557   0.00718  -0.0899   0.7308   0.0769
  -2.500   0.2404   0.01490   0.00640  -0.0893   0.7200   0.0768
  -2.250   0.2664   0.01435   0.00575  -0.0886   0.7102   0.0776
  -2.000   0.2923   0.01389   0.00522  -0.0879   0.7006   0.0787
  -1.750   0.3180   0.01352   0.00483  -0.0873   0.6914   0.0802
  -1.500   0.3426   0.01293   0.00426  -0.0866   0.6828   0.0846
  -1.250   0.3674   0.01260   0.00395  -0.0858   0.6714   0.0889
  -1.000   0.3926   0.01236   0.00368  -0.0851   0.6605   0.0932
  -0.750   0.4178   0.01212   0.00339  -0.0844   0.6502   0.1006
  -0.500   0.4428   0.01185   0.00317  -0.0837   0.6389   0.1208
  -0.250   0.5108   0.00954   0.00314  -0.0927   0.6242   1.0000
   0.000   0.5359   0.00962   0.00309  -0.0920   0.6136   1.0000
   0.250   0.5610   0.00971   0.00307  -0.0913   0.6046   1.0000
   0.500   0.5860   0.00980   0.00307  -0.0907   0.5941   1.0000
   0.750   0.6105   0.00990   0.00309  -0.0899   0.5800   1.0000
   1.000   0.6346   0.01002   0.00309  -0.0890   0.5630   1.0000
   1.250   0.6588   0.01015   0.00313  -0.0883   0.5463   1.0000
   1.500   0.6823   0.01031   0.00317  -0.0873   0.5227   1.0000
   1.750   0.7041   0.01056   0.00323  -0.0861   0.4891   1.0000
   2.000   0.7270   0.01080   0.00334  -0.0851   0.4648   1.0000
   2.250   0.7497   0.01107   0.00349  -0.0841   0.4408   1.0000
   2.500   0.7716   0.01140   0.00366  -0.0830   0.4116   1.0000
   2.750   0.7900   0.01198   0.00394  -0.0814   0.3438   1.0000
   3.000   0.7995   0.01336   0.00460  -0.0786   0.2184   1.0000
   3.250   0.8206   0.01383   0.00496  -0.0775   0.1888   1.0000
   3.750   0.8584   0.01509   0.00586  -0.0748   0.1321   1.0000
   4.000   0.8792   0.01554   0.00631  -0.0736   0.1247   1.0000
   4.250   0.8981   0.01613   0.00690  -0.0722   0.1174   1.0000
   4.500   0.9200   0.01648   0.00730  -0.0713   0.1124   1.0000
   4.750   0.9409   0.01690   0.00778  -0.0702   0.1067   1.0000
   5.000   0.9629   0.01723   0.00816  -0.0692   0.1000   1.0000
   5.250   0.9866   0.01744   0.00843  -0.0684   0.0908   1.0000
   5.500   1.0079   0.01782   0.00864  -0.0674   0.0626   1.0000
   5.750   1.0225   0.01869   0.00951  -0.0653   0.0577   1.0000
   6.000   1.0374   0.01949   0.01039  -0.0631   0.0550   1.0000
   6.250   1.0502   0.02037   0.01138  -0.0608   0.0530   1.0000
   6.500   1.0580   0.02152   0.01261  -0.0577   0.0504   1.0000
   6.750   1.0618   0.02278   0.01389  -0.0541   0.0486   1.0000
   7.000   1.0642   0.02430   0.01540  -0.0504   0.0472   1.0000
   7.250   1.0736   0.02607   0.01713  -0.0479   0.0458   1.0000
   7.500   1.0897   0.02695   0.01811  -0.0462   0.0444   1.0000
   7.750   1.1079   0.02817   0.01938  -0.0449   0.0421   1.0000
   8.000   1.1352   0.02973   0.02092  -0.0450   0.0405   1.0000
   8.250   1.1812   0.03216   0.02327  -0.0481   0.0388   1.0000
   8.500   1.2256   0.03616   0.02733  -0.0514   0.0362   1.0000
   8.750   1.2422   0.03751   0.02895  -0.0496   0.0356   1.0000
   9.000   1.2657   0.04003   0.03171  -0.0491   0.0356   1.0000
   9.250   1.3052   0.04380   0.03555  -0.0508   0.0376   1.0000
   9.500   1.2941   0.04366   0.03625  -0.0440   0.0413   1.0000
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