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E475 (15.01%) (e475-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: E475 (15.01%) (e475-il)
Reynolds number: 50,000
Max Cl/Cd: 20.16 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e475-il-50000.txt
Download as CSV file: xf-e475-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4425   0.12034   0.11134   0.0046   1.0000   0.4248
 -10.250  -0.4090   0.11509   0.10604   0.0040   1.0000   0.4321
 -10.000  -0.4192   0.11362   0.10459   0.0048   1.0000   0.4440
  -9.750  -0.4049   0.11096   0.10190   0.0053   1.0000   0.4580
  -9.500  -0.3856   0.10725   0.09817   0.0052   1.0000   0.4675
  -9.250  -0.3934   0.10559   0.09655   0.0063   1.0000   0.4792
  -9.000  -0.3801   0.10304   0.09398   0.0068   1.0000   0.4925
  -8.750  -0.3608   0.09971   0.09062   0.0068   1.0000   0.5038
  -8.500  -0.3570   0.09743   0.08836   0.0077   1.0000   0.5168
  -8.250  -0.3635   0.09602   0.08699   0.0094   1.0000   0.5308
  -8.000  -0.3386   0.09272   0.08366   0.0091   1.0000   0.5426
  -7.750  -0.6298   0.06755   0.05885  -0.0034   1.0000   0.3564
  -7.500  -0.6688   0.06201   0.05330  -0.0008   1.0000   0.3547
  -7.250  -0.7093   0.05680   0.04800   0.0029   1.0000   0.3548
  -7.000  -0.6869   0.05556   0.04679   0.0044   1.0000   0.3608
  -6.750  -0.6992   0.05234   0.04349   0.0074   1.0000   0.3642
  -6.500  -0.7157   0.04881   0.03980   0.0109   1.0000   0.3672
  -6.250  -0.7314   0.04538   0.03611   0.0145   1.0000   0.3709
  -6.000  -0.7256   0.04329   0.03393   0.0169   1.0000   0.3762
  -5.750  -0.7129   0.04183   0.03243   0.0189   1.0000   0.3825
  -5.500  -0.7132   0.03949   0.02981   0.0217   1.0000   0.3884
  -5.250  -0.7002   0.03790   0.02815   0.0236   1.0000   0.3940
  -5.000  -0.6858   0.03661   0.02681   0.0254   1.0000   0.4010
  -4.750  -0.6794   0.03484   0.02476   0.0278   1.0000   0.4084
  -4.500  -0.6590   0.03391   0.02393   0.0292   1.0000   0.4155
  -4.250  -0.6470   0.03254   0.02234   0.0310   1.0000   0.4233
  -4.000  -0.6289   0.03153   0.02136   0.0325   1.0000   0.4310
  -3.750  -0.6136   0.03050   0.02021   0.0342   1.0000   0.4404
  -3.500  -0.5951   0.02962   0.01936   0.0356   1.0000   0.4489
  -3.250  -0.5788   0.02870   0.01830   0.0370   1.0000   0.4589
  -3.000  -0.5591   0.02799   0.01770   0.0383   1.0000   0.4686
  -2.750  -0.5414   0.02725   0.01691   0.0396   1.0000   0.4799
  -2.500  -0.5225   0.02664   0.01632   0.0408   1.0000   0.4919
  -2.250  -0.5031   0.02609   0.01586   0.0420   1.0000   0.5040
  -2.000  -0.4846   0.02557   0.01541   0.0431   1.0000   0.5182
  -1.750  -0.4665   0.02513   0.01505   0.0443   1.0000   0.5341
  -1.500  -0.4484   0.02475   0.01479   0.0455   1.0000   0.5518
  -1.250  -0.4305   0.02444   0.01464   0.0465   1.0000   0.5719
  -1.000  -0.4139   0.02421   0.01458   0.0475   1.0000   0.5963
  -0.750  -0.3991   0.02407   0.01471   0.0488   1.0000   0.6244
  -0.500  -0.3579   0.02430   0.01540   0.0453   0.9874   0.6752
  -0.250  -0.2364   0.02551   0.01758   0.0309   0.9513   0.7992
   0.000   0.0000   0.02775   0.01995   0.0000   0.9028   0.9028
   0.250   0.2364   0.02550   0.01758  -0.0309   0.7991   0.9513
   0.500   0.3579   0.02430   0.01540  -0.0453   0.6751   0.9874
   0.750   0.3991   0.02407   0.01471  -0.0488   0.6244   1.0000
   1.000   0.4139   0.02421   0.01458  -0.0475   0.5964   1.0000
   1.250   0.4304   0.02444   0.01464  -0.0465   0.5719   1.0000
   1.500   0.4483   0.02474   0.01478  -0.0454   0.5518   1.0000
   1.750   0.4664   0.02513   0.01505  -0.0443   0.5342   1.0000
   2.000   0.4846   0.02557   0.01541  -0.0431   0.5183   1.0000
   2.250   0.5030   0.02608   0.01586  -0.0420   0.5042   1.0000
   2.500   0.5224   0.02664   0.01632  -0.0408   0.4919   1.0000
   2.750   0.5413   0.02725   0.01691  -0.0396   0.4800   1.0000
   3.000   0.5590   0.02799   0.01769  -0.0383   0.4686   1.0000
   3.250   0.5787   0.02870   0.01830  -0.0370   0.4589   1.0000
   3.500   0.5950   0.02961   0.01936  -0.0355   0.4489   1.0000
   3.750   0.6135   0.03050   0.02020  -0.0341   0.4404   1.0000
   4.000   0.6288   0.03154   0.02137  -0.0325   0.4310   1.0000
   4.250   0.6469   0.03253   0.02233  -0.0310   0.4234   1.0000
   4.500   0.6589   0.03390   0.02392  -0.0292   0.4155   1.0000
   4.750   0.6792   0.03484   0.02476  -0.0278   0.4085   1.0000
   5.000   0.6857   0.03661   0.02681  -0.0254   0.4011   1.0000
   5.250   0.7001   0.03790   0.02816  -0.0236   0.3941   1.0000
   5.500   0.7133   0.03948   0.02980  -0.0217   0.3885   1.0000
   5.750   0.7129   0.04183   0.03243  -0.0189   0.3826   1.0000
   6.000   0.7255   0.04328   0.03392  -0.0169   0.3762   1.0000
   6.250   0.7313   0.04536   0.03609  -0.0144   0.3709   1.0000
   6.500   0.7158   0.04880   0.03979  -0.0109   0.3672   1.0000
   6.750   0.6991   0.05234   0.04349  -0.0074   0.3643   1.0000
   7.000   0.6814   0.05594   0.04719  -0.0042   0.3615   1.0000
   7.250   0.6549   0.06016   0.05145  -0.0009   0.3600   1.0000
   7.500   0.6377   0.06394   0.05524   0.0016   0.3580   1.0000
   7.750   0.6297   0.06756   0.05885   0.0034   0.3564   1.0000
   8.000   0.3398   0.09275   0.08369  -0.0092   0.5430   1.0000
   8.250   0.3634   0.09592   0.08689  -0.0094   0.5309   1.0000
   8.500   0.3581   0.09741   0.08834  -0.0078   0.5167   1.0000
   8.750   0.3616   0.09967   0.09058  -0.0069   0.5039   1.0000
   9.000   0.3812   0.10303   0.09397  -0.0069   0.4926   1.0000
   9.250   0.3938   0.10555   0.09650  -0.0064   0.4793   1.0000
   9.500   0.3866   0.10724   0.09816  -0.0053   0.4673   1.0000
   9.750   0.4055   0.11092   0.10186  -0.0054   0.4580   1.0000
  10.000   0.4221   0.11378   0.10475  -0.0050   0.4438   1.0000
  10.250   0.4101   0.11508   0.10602  -0.0041   0.4320   1.0000
  10.500   0.4434   0.12031   0.11131  -0.0047   0.4248   1.0000
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