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EPPLER 793 AIRFOIL (e793-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 793 AIRFOIL (e793-il)
Reynolds number: 50,000
Max Cl/Cd: 30.44 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e793-il-50000-n5.txt
Download as CSV file: xf-e793-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 793 AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3438   0.10306   0.09578  -0.0512   1.0000   0.0606
 -10.500  -0.3770   0.09245   0.08525  -0.0564   1.0000   0.0594
 -10.250  -0.3956   0.08595   0.07883  -0.0588   1.0000   0.0592
 -10.000  -0.4207   0.07913   0.07208  -0.0616   1.0000   0.0589
  -9.750  -0.4497   0.07289   0.06589  -0.0639   1.0000   0.0585
  -9.500  -0.4831   0.06765   0.06067  -0.0653   1.0000   0.0580
  -9.250  -0.5193   0.06390   0.05696  -0.0647   1.0000   0.0575
  -9.000  -0.5500   0.06028   0.05331  -0.0644   1.0000   0.0572
  -8.750  -0.5736   0.05686   0.04976  -0.0636   1.0000   0.0572
  -8.500  -0.5886   0.05373   0.04643  -0.0627   1.0000   0.0574
  -8.250  -0.5973   0.05067   0.04309  -0.0620   1.0000   0.0580
  -8.000  -0.5784   0.04671   0.03861  -0.0659   0.9929   0.0598
  -7.750  -0.5467   0.04461   0.03645  -0.0692   0.9842   0.0625
  -7.500  -0.5166   0.04211   0.03362  -0.0723   0.9746   0.0656
  -7.250  -0.4857   0.03961   0.03069  -0.0748   0.9651   0.0685
  -7.000  -0.4530   0.03781   0.02883  -0.0771   0.9563   0.0718
  -6.750  -0.4212   0.03620   0.02704  -0.0792   0.9462   0.0777
  -6.500  -0.3915   0.03467   0.02545  -0.0808   0.9355   0.0844
  -6.250  -0.3580   0.03311   0.02376  -0.0829   0.9262   0.0941
  -6.000  -0.3255   0.03161   0.02229  -0.0850   0.9161   0.1093
  -5.750  -0.2949   0.03023   0.02090  -0.0868   0.9051   0.1336
  -5.500  -0.2556   0.02893   0.01986  -0.0903   0.8974   0.1743
  -5.250  -0.2260   0.02828   0.01938  -0.0916   0.8853   0.2171
  -5.000  -0.1911   0.02788   0.01894  -0.0933   0.8751   0.2597
  -4.750  -0.1531   0.02768   0.01870  -0.0951   0.8663   0.2952
  -4.500  -0.1216   0.02756   0.01849  -0.0957   0.8549   0.3243
  -4.250  -0.0816   0.02738   0.01823  -0.0974   0.8474   0.3513
  -4.000  -0.0535   0.02726   0.01800  -0.0973   0.8349   0.3730
  -3.750  -0.0205   0.02702   0.01757  -0.0980   0.8245   0.3950
  -3.500   0.0143   0.02677   0.01722  -0.0988   0.8151   0.4141
  -3.250   0.0427   0.02662   0.01696  -0.0986   0.8032   0.4312
  -3.000   0.0777   0.02634   0.01654  -0.0994   0.7942   0.4489
  -2.750   0.1070   0.02616   0.01623  -0.0995   0.7826   0.4652
  -2.500   0.1352   0.02603   0.01604  -0.0992   0.7712   0.4796
  -2.250   0.1701   0.02575   0.01563  -0.0999   0.7626   0.4955
  -2.000   0.1953   0.02569   0.01550  -0.0992   0.7500   0.5095
  -1.750   0.2246   0.02556   0.01526  -0.0992   0.7394   0.5247
  -1.500   0.2563   0.02538   0.01496  -0.0995   0.7297   0.5404
  -1.250   0.2820   0.02537   0.01487  -0.0990   0.7178   0.5557
  -1.000   0.3131   0.02524   0.01463  -0.0992   0.7085   0.5721
  -0.750   0.3398   0.02523   0.01455  -0.0988   0.6976   0.5883
  -0.500   0.3656   0.02525   0.01452  -0.0982   0.6870   0.6043
  -0.250   0.3959   0.02515   0.01434  -0.0981   0.6781   0.6221
   0.000   0.4187   0.02528   0.01447  -0.0972   0.6670   0.6392
   0.250   0.4482   0.02520   0.01432  -0.0970   0.6587   0.6585
   0.500   0.4702   0.02534   0.01449  -0.0958   0.6480   0.6772
   0.750   0.4956   0.02537   0.01451  -0.0950   0.6393   0.6979
   1.000   0.5192   0.02545   0.01460  -0.0940   0.6298   0.7204
   1.250   0.5420   0.02555   0.01472  -0.0928   0.6208   0.7450
   1.500   0.5645   0.02558   0.01478  -0.0914   0.6124   0.7720
   1.750   0.5842   0.02569   0.01495  -0.0896   0.6038   0.8028
   2.000   0.6058   0.02568   0.01499  -0.0880   0.5955   0.8414
   2.250   0.6306   0.02574   0.01512  -0.0872   0.5871   0.8970
   2.500   0.6702   0.02583   0.01514  -0.0897   0.5784   1.0000
   2.750   0.6978   0.02630   0.01549  -0.0905   0.5697   1.0000
   3.000   0.7272   0.02667   0.01572  -0.0912   0.5617   1.0000
   3.250   0.7534   0.02718   0.01614  -0.0914   0.5538   1.0000
   3.500   0.7796   0.02766   0.01653  -0.0915   0.5458   1.0000
   3.750   0.8071   0.02810   0.01688  -0.0917   0.5386   1.0000
   4.000   0.8292   0.02875   0.01751  -0.0912   0.5303   1.0000
   4.250   0.8621   0.02896   0.01758  -0.0919   0.5246   1.0000
   4.500   0.8768   0.02994   0.01864  -0.0906   0.5154   1.0000
   4.750   0.9073   0.03023   0.01884  -0.0909   0.5094   1.0000
   5.000   0.9235   0.03120   0.01986  -0.0898   0.5013   1.0000
   5.250   0.9491   0.03171   0.02036  -0.0896   0.4947   1.0000
   5.500   0.9720   0.03237   0.02102  -0.0891   0.4881   1.0000
   5.750   0.9889   0.03331   0.02201  -0.0880   0.4805   1.0000
   6.000   1.0210   0.03354   0.02220  -0.0884   0.4753   1.0000
   6.250   1.0279   0.03498   0.02377  -0.0863   0.4670   1.0000
   6.500   1.0533   0.03551   0.02430  -0.0860   0.4610   1.0000
   6.750   1.0718   0.03643   0.02527  -0.0851   0.4547   1.0000
   7.000   1.0820   0.03772   0.02668  -0.0833   0.4473   1.0000
   7.250   1.1150   0.03787   0.02680  -0.0838   0.4424   1.0000
   7.500   1.1103   0.03998   0.02908  -0.0807   0.4343   1.0000
   7.750   1.1312   0.04073   0.02987  -0.0799   0.4284   1.0000
   8.000   1.1546   0.04137   0.03056  -0.0795   0.4231   1.0000
   8.250   1.1371   0.04406   0.03342  -0.0753   0.4148   1.0000
   8.500   1.1714   0.04408   0.03346  -0.0757   0.4101   1.0000
   8.750   1.1373   0.04806   0.03760  -0.0709   0.4016   1.0000
   9.000   1.1532   0.04908   0.03868  -0.0699   0.3956   1.0000
   9.250   1.2062   0.04774   0.03736  -0.0712   0.3921   1.0000
   9.500   1.1207   0.05645   0.04626  -0.0660   0.3797   1.0000
   9.750   1.1723   0.05437   0.04422  -0.0659   0.3768   1.0000
  10.000   1.0930   0.06497   0.05494  -0.0647   0.3626   1.0000
  10.250   1.1384   0.06278   0.05282  -0.0637   0.3603   1.0000
  10.750   1.1160   0.07138   0.06158  -0.0634   0.3436   1.0000
  11.750   1.0267   0.09808   0.08859  -0.0691   0.3005   1.0000
  12.000   1.0559   0.09714   0.08776  -0.0678   0.2973   1.0000
  12.500   1.0533   0.10475   0.09553  -0.0692   0.2818   1.0000
  13.000   1.0515   0.11238   0.10332  -0.0709   0.2666   1.0000
  13.250   1.0264   0.12034   0.11133  -0.0739   0.2552   1.0000
  13.500   1.0520   0.11970   0.11080  -0.0727   0.2514   1.0000
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