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E475 (15.01%) (e475-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E475 (15.01%) (e475-il)
Reynolds number: 50,000
Max Cl/Cd: 24.1 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e475-il-50000-n5.txt
Download as CSV file: xf-e475-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E475  (15.01%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.6402   0.09754   0.08844  -0.0246   1.0000   0.1762
 -11.750  -0.6276   0.09611   0.08697  -0.0239   1.0000   0.1795
 -11.500  -0.7778   0.07009   0.06104  -0.0393   1.0000   0.1896
 -11.250  -0.7188   0.07492   0.06583  -0.0347   1.0000   0.1917
 -11.000  -0.7036   0.07417   0.06506  -0.0335   1.0000   0.1951
 -10.750  -0.8195   0.05969   0.05051  -0.0373   1.0000   0.1996
 -10.500  -0.8841   0.05437   0.04504  -0.0317   1.0000   0.2018
 -10.250  -0.9326   0.05011   0.04043  -0.0255   1.0000   0.2049
 -10.000  -0.9075   0.04986   0.04027  -0.0246   1.0000   0.2085
  -9.750  -0.9016   0.04861   0.03896  -0.0221   1.0000   0.2123
  -9.500  -0.9092   0.04653   0.03668  -0.0184   1.0000   0.2165
  -9.250  -0.9270   0.04387   0.03362  -0.0135   1.0000   0.2210
  -9.000  -0.9046   0.04339   0.03322  -0.0124   1.0000   0.2247
  -8.750  -0.8933   0.04237   0.03213  -0.0102   1.0000   0.2291
  -8.500  -0.8909   0.04076   0.03028  -0.0071   1.0000   0.2339
  -8.250  -0.8860   0.03924   0.02853  -0.0042   1.0000   0.2386
  -8.000  -0.8674   0.03856   0.02789  -0.0026   1.0000   0.2428
  -7.750  -0.8554   0.03753   0.02672  -0.0004   1.0000   0.2477
  -7.500  -0.8492   0.03609   0.02495   0.0025   1.0000   0.2533
  -7.250  -0.8306   0.03533   0.02423   0.0040   1.0000   0.2574
  -7.000  -0.8138   0.03455   0.02341   0.0057   1.0000   0.2623
  -6.750  -0.8012   0.03351   0.02215   0.0079   1.0000   0.2683
  -6.500  -0.7846   0.03265   0.02121   0.0096   1.0000   0.2731
  -6.250  -0.7658   0.03196   0.02052   0.0111   1.0000   0.2780
  -6.000  -0.7496   0.03115   0.01955   0.0129   1.0000   0.2840
  -5.750  -0.7322   0.03039   0.01870   0.0145   1.0000   0.2897
  -5.500  -0.7126   0.02979   0.01812   0.0159   1.0000   0.2950
  -5.250  -0.6946   0.02910   0.01731   0.0174   1.0000   0.3013
  -5.000  -0.6754   0.02847   0.01664   0.0188   1.0000   0.3073
  -4.750  -0.6556   0.02795   0.01613   0.0201   1.0000   0.3134
  -4.500  -0.6368   0.02737   0.01542   0.0215   1.0000   0.3207
  -4.250  -0.6159   0.02688   0.01501   0.0227   1.0000   0.3266
  -4.000  -0.5959   0.02642   0.01453   0.0239   1.0000   0.3339
  -3.750  -0.5756   0.02597   0.01408   0.0251   1.0000   0.3414
  -3.500  -0.5550   0.02559   0.01375   0.0262   1.0000   0.3492
  -3.250  -0.5344   0.02523   0.01336   0.0273   1.0000   0.3576
  -3.000  -0.5134   0.02491   0.01313   0.0283   1.0000   0.3660
  -2.750  -0.4928   0.02463   0.01288   0.0293   1.0000   0.3756
  -2.500  -0.4722   0.02438   0.01270   0.0303   1.0000   0.3859
  -2.250  -0.4390   0.02420   0.01263   0.0288   0.9946   0.3984
  -2.000  -0.3827   0.02405   0.01261   0.0230   0.9779   0.4172
  -1.750  -0.3302   0.02377   0.01249   0.0181   0.9596   0.4386
  -1.500  -0.2797   0.02337   0.01231   0.0139   0.9407   0.4629
  -1.250  -0.2352   0.02289   0.01208   0.0110   0.9197   0.4915
  -1.000  -0.1980   0.02234   0.01181   0.0098   0.8946   0.5236
  -0.750  -0.1637   0.02177   0.01156   0.0093   0.8667   0.5632
  -0.500  -0.1279   0.02117   0.01134   0.0089   0.8357   0.6132
  -0.250  -0.0785   0.02067   0.01127   0.0067   0.8001   0.6782
   0.000   0.0000   0.02049   0.01133   0.0000   0.7502   0.7502
   0.250   0.0785   0.02067   0.01126  -0.0067   0.6781   0.8000
   0.500   0.1279   0.02117   0.01134  -0.0090   0.6130   0.8356
   0.750   0.1637   0.02177   0.01155  -0.0093   0.5630   0.8667
   1.000   0.1981   0.02234   0.01181  -0.0098   0.5235   0.8947
   1.250   0.2352   0.02289   0.01208  -0.0110   0.4915   0.9197
   1.500   0.2795   0.02337   0.01231  -0.0138   0.4630   0.9406
   1.750   0.3301   0.02376   0.01249  -0.0181   0.4387   0.9596
   2.000   0.3827   0.02405   0.01261  -0.0230   0.4172   0.9780
   2.250   0.4390   0.02420   0.01263  -0.0288   0.3985   0.9946
   2.500   0.4721   0.02438   0.01270  -0.0303   0.3859   1.0000
   2.750   0.4927   0.02463   0.01287  -0.0293   0.3757   1.0000
   3.000   0.5133   0.02491   0.01313  -0.0283   0.3660   1.0000
   3.250   0.5343   0.02523   0.01336  -0.0273   0.3576   1.0000
   3.500   0.5549   0.02559   0.01375  -0.0262   0.3491   1.0000
   3.750   0.5755   0.02597   0.01407  -0.0251   0.3414   1.0000
   4.000   0.5958   0.02642   0.01453  -0.0239   0.3340   1.0000
   4.250   0.6158   0.02688   0.01500  -0.0226   0.3266   1.0000
   4.500   0.6367   0.02737   0.01542  -0.0215   0.3207   1.0000
   4.750   0.6555   0.02794   0.01613  -0.0201   0.3134   1.0000
   5.000   0.6753   0.02847   0.01663  -0.0188   0.3072   1.0000
   5.250   0.6946   0.02909   0.01731  -0.0174   0.3014   1.0000
   5.500   0.7125   0.02979   0.01812  -0.0158   0.2951   1.0000
   5.750   0.7321   0.03038   0.01869  -0.0145   0.2897   1.0000
   6.000   0.7496   0.03115   0.01956  -0.0129   0.2841   1.0000
   6.250   0.7657   0.03196   0.02052  -0.0111   0.2780   1.0000
   6.500   0.7845   0.03265   0.02121  -0.0096   0.2731   1.0000
   6.750   0.8011   0.03351   0.02214  -0.0079   0.2682   1.0000
   7.000   0.8137   0.03455   0.02341  -0.0057   0.2624   1.0000
   7.250   0.8305   0.03532   0.02422  -0.0039   0.2574   1.0000
   7.500   0.8492   0.03609   0.02495  -0.0025   0.2533   1.0000
   7.750   0.8554   0.03752   0.02671   0.0004   0.2478   1.0000
   8.000   0.8674   0.03856   0.02790   0.0026   0.2428   1.0000
   8.250   0.8858   0.03925   0.02854   0.0042   0.2386   1.0000
   8.500   0.8909   0.04075   0.03027   0.0071   0.2339   1.0000
   8.750   0.8934   0.04236   0.03212   0.0102   0.2291   1.0000
   9.000   0.9046   0.04338   0.03322   0.0124   0.2248   1.0000
   9.500   0.9092   0.04652   0.03667   0.0184   0.2165   1.0000
   9.750   0.9017   0.04860   0.03895   0.0221   0.2123   1.0000
  10.000   0.9082   0.04981   0.04022   0.0245   0.2084   1.0000
  10.250   0.9325   0.05011   0.04043   0.0255   0.2048   1.0000
  10.500   0.8846   0.05435   0.04501   0.0317   0.2018   1.0000
  10.750   0.8202   0.05968   0.05050   0.0372   0.1995   1.0000
  11.000   0.7081   0.07358   0.06447   0.0338   0.1951   1.0000
  11.250   0.7212   0.07465   0.06556   0.0348   0.1918   1.0000
  11.500   0.7877   0.06904   0.05998   0.0397   0.1895   1.0000
  11.750   0.6283   0.09614   0.08701   0.0238   0.1796   1.0000
  12.000   0.6421   0.09736   0.08826   0.0246   0.1762   1.0000
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