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EPPLER 593 AIRFOIL (e593-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 593 AIRFOIL (e593-il)
Reynolds number: 500,000
Max Cl/Cd: 113.45 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e593-il-500000-n5.txt
Download as CSV file: xf-e593-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 593 AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3850   0.09432   0.09034   0.0035   0.4744   0.0069
  -8.500  -0.3843   0.09010   0.08615   0.0015   0.4731   0.0067
  -8.000  -0.5593   0.02863   0.02353  -0.0376   0.4800   0.0052
  -7.750  -0.5403   0.02549   0.01997  -0.0379   0.4784   0.0052
  -7.500  -0.5186   0.02328   0.01742  -0.0379   0.4765   0.0053
  -7.250  -0.4954   0.02157   0.01540  -0.0377   0.4745   0.0053
  -7.000  -0.4710   0.02019   0.01376  -0.0374   0.4723   0.0054
  -6.750  -0.4459   0.01907   0.01240  -0.0371   0.4701   0.0054
  -6.500  -0.4202   0.01810   0.01123  -0.0368   0.4682   0.0055
  -6.250  -0.3940   0.01727   0.01020  -0.0365   0.4664   0.0055
  -6.000  -0.3675   0.01655   0.00932  -0.0363   0.4648   0.0056
  -5.750  -0.3409   0.01575   0.00839  -0.0360   0.4632   0.0058
  -5.500  -0.3140   0.01506   0.00759  -0.0357   0.4616   0.0060
  -5.250  -0.2866   0.01454   0.00696  -0.0355   0.4599   0.0063
  -5.000  -0.2591   0.01408   0.00640  -0.0352   0.4581   0.0066
  -4.750  -0.2314   0.01366   0.00588  -0.0350   0.4563   0.0071
  -4.500  -0.2036   0.01329   0.00541  -0.0348   0.4544   0.0076
  -4.250  -0.1759   0.01289   0.00493  -0.0345   0.4527   0.0085
  -4.000  -0.1481   0.01259   0.00454  -0.0343   0.4511   0.0098
  -3.750  -0.1202   0.01228   0.00419  -0.0341   0.4495   0.0126
  -3.500  -0.0922   0.01199   0.00389  -0.0339   0.4483   0.0170
  -3.250  -0.0642   0.01174   0.00365  -0.0337   0.4469   0.0232
  -3.000  -0.0362   0.01151   0.00346  -0.0336   0.4454   0.0316
  -2.750  -0.0080   0.01133   0.00329  -0.0335   0.4439   0.0414
  -2.500   0.0201   0.01116   0.00317  -0.0334   0.4422   0.0521
  -2.250   0.0484   0.01102   0.00303  -0.0332   0.4404   0.0603
  -2.000   0.0767   0.01091   0.00290  -0.0331   0.4388   0.0680
  -1.750   0.1049   0.01080   0.00278  -0.0330   0.4374   0.0763
  -1.500   0.1333   0.01072   0.00268  -0.0329   0.4360   0.0847
  -1.250   0.1615   0.01067   0.00261  -0.0328   0.4346   0.0942
  -1.000   0.1899   0.01059   0.00255  -0.0327   0.4334   0.1050
  -0.750   0.2183   0.01051   0.00250  -0.0326   0.4322   0.1155
  -0.500   0.2468   0.01045   0.00245  -0.0325   0.4307   0.1266
  -0.250   0.2752   0.01038   0.00241  -0.0325   0.4291   0.1403
   0.000   0.3036   0.01030   0.00238  -0.0324   0.4274   0.1572
   0.250   0.3319   0.01023   0.00236  -0.0324   0.4259   0.1781
   0.500   0.3602   0.01015   0.00235  -0.0323   0.4245   0.2073
   0.750   0.3883   0.01006   0.00235  -0.0323   0.4232   0.2451
   1.000   0.4163   0.00994   0.00237  -0.0322   0.4219   0.3011
   1.250   0.4433   0.00963   0.00239  -0.0322   0.4206   0.4226
   1.750   0.5190   0.00829   0.00250  -0.0360   0.4175   1.0000
   2.000   0.5464   0.00837   0.00255  -0.0358   0.4160   1.0000
   2.250   0.5738   0.00845   0.00260  -0.0355   0.4145   1.0000
   2.500   0.6012   0.00853   0.00266  -0.0353   0.4131   1.0000
   2.750   0.6287   0.00861   0.00272  -0.0351   0.4115   1.0000
   3.000   0.6562   0.00869   0.00278  -0.0349   0.4098   1.0000
   3.250   0.6838   0.00877   0.00284  -0.0347   0.4082   1.0000
   3.500   0.7113   0.00887   0.00291  -0.0345   0.4068   1.0000
   3.750   0.7388   0.00899   0.00299  -0.0344   0.4052   1.0000
   4.000   0.7663   0.00910   0.00310  -0.0342   0.4036   1.0000
   4.250   0.7940   0.00918   0.00321  -0.0341   0.4018   1.0000
   4.500   0.8217   0.00927   0.00332  -0.0341   0.3996   1.0000
   4.750   0.8494   0.00935   0.00342  -0.0340   0.3971   1.0000
   5.000   0.8771   0.00942   0.00351  -0.0339   0.3944   1.0000
   5.250   0.9047   0.00951   0.00358  -0.0338   0.3918   1.0000
   5.500   0.9321   0.00962   0.00368  -0.0337   0.3893   1.0000
   5.750   0.9599   0.00971   0.00384  -0.0336   0.3864   1.0000
   6.000   0.9875   0.00979   0.00397  -0.0336   0.3831   1.0000
   6.250   1.0151   0.00988   0.00408  -0.0336   0.3796   1.0000
   6.500   1.0424   0.00998   0.00418  -0.0335   0.3761   1.0000
   6.750   1.0700   0.01009   0.00435  -0.0335   0.3721   1.0000
   7.000   1.0974   0.01019   0.00450  -0.0334   0.3678   1.0000
   7.250   1.1247   0.01031   0.00464  -0.0334   0.3634   1.0000
   7.500   1.1519   0.01044   0.00482  -0.0333   0.3587   1.0000
   8.000   1.2060   0.01072   0.00518  -0.0333   0.3448   1.0000
   8.250   1.2328   0.01089   0.00538  -0.0332   0.3358   1.0000
   8.500   1.2593   0.01110   0.00562  -0.0332   0.3256   1.0000
   8.750   1.2851   0.01138   0.00590  -0.0331   0.3117   1.0000
   9.000   1.3101   0.01177   0.00625  -0.0329   0.2938   1.0000
   9.250   1.3336   0.01234   0.00675  -0.0327   0.2704   1.0000
   9.500   1.3552   0.01314   0.00744  -0.0324   0.2435   1.0000
   9.750   1.3758   0.01403   0.00824  -0.0321   0.2189   1.0000
  10.000   1.3959   0.01494   0.00908  -0.0317   0.1970   1.0000
  10.250   1.4149   0.01589   0.00998  -0.0313   0.1774   1.0000
  10.500   1.4328   0.01690   0.01094  -0.0307   0.1583   1.0000
  10.750   1.4487   0.01801   0.01200  -0.0301   0.1414   1.0000
  11.000   1.4631   0.01917   0.01313  -0.0294   0.1272   1.0000
  11.250   1.4749   0.02044   0.01439  -0.0285   0.1146   1.0000
  11.500   1.4828   0.02192   0.01588  -0.0276   0.1036   1.0000
  11.750   1.4795   0.02400   0.01803  -0.0262   0.0959   1.0000
  12.000   1.4667   0.02820   0.02231  -0.0275   0.0907   1.0000
  12.250   1.4584   0.03188   0.02605  -0.0281   0.0854   1.0000
  12.500   1.4497   0.03539   0.02961  -0.0283   0.0807   1.0000
  12.750   1.4398   0.03895   0.03320  -0.0284   0.0765   1.0000
  13.000   1.4326   0.04221   0.03650  -0.0285   0.0719   1.0000
  13.250   1.4236   0.04567   0.03999  -0.0286   0.0676   1.0000
  13.500   1.4179   0.04884   0.04320  -0.0288   0.0638   1.0000
  13.750   1.4125   0.05201   0.04640  -0.0290   0.0596   1.0000
  14.000   1.4065   0.05533   0.04975  -0.0294   0.0560   1.0000
  14.250   1.4060   0.05821   0.05270  -0.0297   0.0532   1.0000
  14.500   1.4024   0.06155   0.05606  -0.0303   0.0491   1.0000
  14.750   1.4015   0.06463   0.05918  -0.0309   0.0459   1.0000
  15.000   1.4006   0.06780   0.06240  -0.0315   0.0430   1.0000
  15.250   1.3983   0.07119   0.06581  -0.0323   0.0397   1.0000
  15.500   1.3981   0.07439   0.06906  -0.0330   0.0368   1.0000
  15.750   1.3965   0.07780   0.07250  -0.0338   0.0339   1.0000
  16.000   1.3954   0.08122   0.07598  -0.0347   0.0319   1.0000
  16.250   1.3952   0.08456   0.07937  -0.0357   0.0293   1.0000
  16.500   1.3925   0.08836   0.08321  -0.0368   0.0273   1.0000
  16.750   1.3925   0.09177   0.08669  -0.0379   0.0255   1.0000
  17.000   1.3908   0.09547   0.09046  -0.0391   0.0237   1.0000
  17.250   1.3880   0.09943   0.09446  -0.0404   0.0218   1.0000
  17.500   1.3867   0.10321   0.09830  -0.0418   0.0198   1.0000
  17.750   1.3834   0.10735   0.10248  -0.0433   0.0182   1.0000
  18.000   1.3815   0.11132   0.10652  -0.0448   0.0169   1.0000
  18.250   1.3796   0.11534   0.11062  -0.0465   0.0158   1.0000
  18.500   1.3754   0.11982   0.11514  -0.0484   0.0144   1.0000
  18.750   1.3740   0.12388   0.11929  -0.0501   0.0138   1.0000
  19.000   1.3710   0.12820   0.12368  -0.0521   0.0125   1.0000
  19.250   1.3681   0.13258   0.12814  -0.0542   0.0119   1.0000
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