Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

E193 (10.22%) (e193-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: E193 (10.22%) (e193-il)
Reynolds number: 500,000
Max Cl/Cd: 107.16 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e193-il-500000-n5.txt
Download as CSV file: xf-e193-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E193  (10.22%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2907   0.07776   0.07565  -0.0402   1.0000   0.0091
  -9.250  -0.3744   0.08660   0.08435  -0.0380   1.0000   0.0090
  -9.000  -0.3773   0.08274   0.08052  -0.0393   1.0000   0.0089
  -8.750  -0.3799   0.07930   0.07712  -0.0403   1.0000   0.0088
  -8.500  -0.3821   0.07488   0.07273  -0.0428   0.9932   0.0087
  -8.250  -0.3742   0.06799   0.06585  -0.0516   0.9764   0.0085
  -8.000  -0.3617   0.05697   0.05478  -0.0689   0.9434   0.0083
  -7.750  -0.3917   0.03195   0.02883  -0.0858   0.8895   0.0077
  -7.500  -0.3891   0.02598   0.02209  -0.0854   0.8617   0.0078
  -7.250  -0.3752   0.02287   0.01843  -0.0844   0.8406   0.0080
  -7.000  -0.3569   0.02073   0.01584  -0.0836   0.8221   0.0082
  -6.750  -0.3361   0.01913   0.01385  -0.0828   0.8058   0.0084
  -6.500  -0.3138   0.01782   0.01220  -0.0821   0.7912   0.0086
  -6.250  -0.2904   0.01673   0.01083  -0.0815   0.7776   0.0087
  -6.000  -0.2663   0.01585   0.00970  -0.0809   0.7652   0.0089
  -5.750  -0.2413   0.01514   0.00879  -0.0804   0.7535   0.0091
  -5.500  -0.2159   0.01456   0.00803  -0.0801   0.7424   0.0094
  -5.250  -0.1919   0.01354   0.00684  -0.0795   0.7325   0.0098
  -5.000  -0.1668   0.01290   0.00608  -0.0791   0.7228   0.0101
  -4.750  -0.1411   0.01235   0.00544  -0.0787   0.7138   0.0104
  -4.500  -0.1152   0.01190   0.00488  -0.0784   0.7054   0.0107
  -4.250  -0.0890   0.01148   0.00437  -0.0781   0.6970   0.0111
  -4.000  -0.0626   0.01114   0.00393  -0.0778   0.6896   0.0115
  -3.750  -0.0359   0.01082   0.00353  -0.0776   0.6820   0.0121
  -3.500  -0.0090   0.01057   0.00319  -0.0773   0.6751   0.0126
  -3.250   0.0181   0.01034   0.00287  -0.0772   0.6681   0.0133
  -3.000   0.0450   0.01010   0.00256  -0.0769   0.6618   0.0152
  -2.750   0.0723   0.00992   0.00233  -0.0768   0.6553   0.0175
  -2.500   0.0992   0.00966   0.00210  -0.0766   0.6492   0.0311
  -2.250   0.1262   0.00942   0.00194  -0.0765   0.6436   0.0608
  -2.000   0.1531   0.00920   0.00182  -0.0764   0.6375   0.0944
  -1.500   0.2068   0.00872   0.00164  -0.0762   0.6266   0.2016
  -1.250   0.2336   0.00851   0.00158  -0.0762   0.6211   0.2583
  -1.000   0.2602   0.00829   0.00154  -0.0760   0.6160   0.3277
  -0.750   0.2867   0.00804   0.00152  -0.0759   0.6107   0.4087
  -0.500   0.3130   0.00782   0.00151  -0.0757   0.6056   0.4887
  -0.250   0.3393   0.00763   0.00151  -0.0754   0.6006   0.5602
   0.000   0.3650   0.00741   0.00152  -0.0750   0.5954   0.6442
   0.250   0.3890   0.00715   0.00156  -0.0741   0.5906   0.7437
   0.500   0.4115   0.00688   0.00161  -0.0727   0.5859   0.8530
   0.750   0.4509   0.00680   0.00166  -0.0748   0.5804   0.9501
   1.000   0.4912   0.00685   0.00166  -0.0775   0.5753   0.9833
   1.250   0.5321   0.00689   0.00166  -0.0804   0.5699   0.9981
   1.500   0.5602   0.00696   0.00170  -0.0805   0.5646   1.0000
   1.750   0.5857   0.00705   0.00173  -0.0800   0.5597   1.0000
   2.000   0.6116   0.00711   0.00179  -0.0796   0.5541   1.0000
   2.250   0.6373   0.00719   0.00185  -0.0792   0.5479   1.0000
   2.500   0.6631   0.00728   0.00191  -0.0787   0.5416   1.0000
   2.750   0.6890   0.00737   0.00197  -0.0783   0.5340   1.0000
   3.000   0.7149   0.00747   0.00206  -0.0779   0.5262   1.0000
   3.250   0.7406   0.00757   0.00214  -0.0775   0.5174   1.0000
   3.500   0.7667   0.00767   0.00223  -0.0772   0.5087   1.0000
   3.750   0.7923   0.00780   0.00233  -0.0768   0.4991   1.0000
   4.000   0.8180   0.00793   0.00245  -0.0764   0.4880   1.0000
   4.250   0.8438   0.00805   0.00257  -0.0760   0.4766   1.0000
   4.500   0.8694   0.00820   0.00271  -0.0756   0.4644   1.0000
   4.750   0.8947   0.00837   0.00287  -0.0752   0.4499   1.0000
   5.000   0.9194   0.00858   0.00303  -0.0746   0.4314   1.0000
   5.250   0.9427   0.00889   0.00323  -0.0739   0.4016   1.0000
   5.500   0.9630   0.00945   0.00353  -0.0727   0.3467   1.0000
   5.750   0.9796   0.01035   0.00404  -0.0711   0.2714   1.0000
   6.000   0.9981   0.01111   0.00454  -0.0698   0.2178   1.0000
   6.250   1.0179   0.01176   0.00500  -0.0686   0.1782   1.0000
   6.500   1.0360   0.01252   0.00553  -0.0673   0.1348   1.0000
   7.000   1.0721   0.01399   0.00664  -0.0645   0.0682   1.0000
   7.250   1.0905   0.01466   0.00719  -0.0632   0.0463   1.0000
   7.500   1.1066   0.01546   0.00786  -0.0615   0.0230   1.0000
   7.750   1.1232   0.01620   0.00854  -0.0599   0.0120   1.0000
   8.000   1.1417   0.01676   0.00914  -0.0585   0.0102   1.0000
   8.250   1.1598   0.01733   0.00975  -0.0571   0.0092   1.0000
   8.500   1.1775   0.01788   0.01037  -0.0556   0.0085   1.0000
   8.750   1.1939   0.01845   0.01100  -0.0540   0.0080   1.0000
   9.000   1.2074   0.01907   0.01169  -0.0518   0.0077   1.0000
   9.250   1.2193   0.01977   0.01245  -0.0495   0.0074   1.0000
   9.500   1.2300   0.02055   0.01332  -0.0471   0.0071   1.0000
   9.750   1.2395   0.02145   0.01429  -0.0447   0.0068   1.0000
  10.000   1.2460   0.02257   0.01550  -0.0422   0.0066   1.0000
  10.250   1.2529   0.02372   0.01673  -0.0399   0.0065   1.0000
  10.500   1.2612   0.02485   0.01795  -0.0380   0.0064   1.0000
  10.750   1.2687   0.02609   0.01928  -0.0362   0.0063   1.0000
  11.000   1.2748   0.02752   0.02080  -0.0345   0.0062   1.0000
  11.250   1.2812   0.02901   0.02240  -0.0330   0.0061   1.0000
  11.500   1.2872   0.03062   0.02410  -0.0316   0.0060   1.0000
  11.750   1.2909   0.03250   0.02607  -0.0303   0.0059   1.0000
  12.000   1.2949   0.03443   0.02810  -0.0292   0.0058   1.0000
  12.250   1.2983   0.03651   0.03028  -0.0283   0.0058   1.0000
  12.500   1.3015   0.03866   0.03254  -0.0274   0.0057   1.0000
  12.750   1.3045   0.04090   0.03488  -0.0268   0.0056   1.0000
  13.000   1.3067   0.04328   0.03736  -0.0262   0.0055   1.0000
  13.250   1.3090   0.04572   0.03990  -0.0257   0.0053   1.0000
  13.500   1.3107   0.04828   0.04258  -0.0254   0.0053   1.0000
  13.750   1.3119   0.05094   0.04535  -0.0252   0.0051   1.0000
  14.000   1.3126   0.05377   0.04828  -0.0252   0.0050   1.0000
  14.250   1.3131   0.05669   0.05131  -0.0252   0.0050   1.0000
  14.500   1.3135   0.05969   0.05441  -0.0256   0.0048   1.0000
  14.750   1.3119   0.06307   0.05791  -0.0259   0.0048   1.0000
  15.000   1.3108   0.06648   0.06142  -0.0266   0.0048   1.0000
  15.250   1.3074   0.07030   0.06537  -0.0273   0.0047   1.0000
  15.500   1.3046   0.07416   0.06935  -0.0283   0.0047   1.0000
  15.750   1.3003   0.07839   0.07371  -0.0294   0.0046   1.0000
  16.000   1.2948   0.08291   0.07836  -0.0308   0.0046   1.0000
  16.250   1.2889   0.08763   0.08321  -0.0324   0.0046   1.0000
  16.500   1.2808   0.09285   0.08857  -0.0344   0.0045   1.0000
  16.750   1.2735   0.09813   0.09399  -0.0366   0.0045   1.0000
  17.000   1.2666   0.10351   0.09951  -0.0390   0.0045   1.0000
  17.250   1.2571   0.10949   0.10564  -0.0418   0.0045   1.0000
  17.500   1.2455   0.11604   0.11235  -0.0451   0.0044   1.0000
  17.750   1.2372   0.12224   0.11871  -0.0484   0.0045   1.0000
  18.000   1.2257   0.12919   0.12581  -0.0522   0.0044   1.0000
  18.250   1.2154   0.13612   0.13287  -0.0562   0.0044   1.0000
  18.500   1.2037   0.14360   0.14050  -0.0607   0.0044   1.0000
  18.750   1.1923   0.15124   0.14828  -0.0653   0.0044   1.0000
  19.000   1.1812   0.15910   0.15628  -0.0702   0.0044   1.0000
<< Back to E193 (10.22%) (e193-il)

Polar data table (+)

Polar graphs


<< Back to E193 (10.22%) (e193-il)