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EPPLER 340 AIRFOIL (e340-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 340 AIRFOIL (e340-il)
Reynolds number: 50,000
Max Cl/Cd: 13.57 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e340-il-50000.txt
Download as CSV file: xf-e340-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 340 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4709   0.11094   0.10515   0.0194   1.0000   0.2896
  -9.000  -0.4664   0.10762   0.10189   0.0198   1.0000   0.3076
  -8.750  -0.4709   0.10485   0.09923   0.0201   1.0000   0.3288
  -8.500  -0.4602   0.10116   0.09562   0.0215   1.0000   0.3515
  -8.250  -0.4591   0.09871   0.09325   0.0230   1.0000   0.3799
  -8.000  -0.4382   0.09521   0.08980   0.0254   1.0000   0.4116
  -7.750  -0.4446   0.09341   0.08813   0.0281   1.0000   0.4483
  -7.500  -0.4070   0.08987   0.08461   0.0314   1.0000   0.4971
  -6.500  -0.4202   0.07275   0.06797   0.0246   1.0000   0.4773
  -6.250  -0.5070   0.06503   0.06051   0.0158   1.0000   0.4023
  -6.000  -0.5617   0.05909   0.05427   0.0098   1.0000   0.3057
  -5.750  -0.5949   0.05886   0.05415   0.0157   1.0000   0.3044
  -5.500  -0.6124   0.05493   0.04890   0.0150   0.9949   0.1843
  -5.250  -0.5573   0.04857   0.04129   0.0103   0.9749   0.1255
  -5.000  -0.5038   0.04389   0.03573   0.0060   0.9562   0.1103
  -4.750  -0.4505   0.04009   0.03131   0.0018   0.9366   0.1076
  -4.500  -0.3920   0.03674   0.02737  -0.0028   0.9182   0.1087
  -4.250  -0.3297   0.03366   0.02376  -0.0074   0.8994   0.1114
  -4.000   0.0237   0.02721   0.02003  -0.0430   0.8901   1.0000
  -3.750   0.0417   0.02723   0.01960  -0.0416   0.8583   1.0000
  -3.500   0.0607   0.02727   0.01926  -0.0406   0.8320   1.0000
  -3.250   0.0793   0.02735   0.01899  -0.0394   0.8108   1.0000
  -3.000   0.0992   0.02744   0.01878  -0.0385   0.7920   1.0000
  -2.750   0.1205   0.02756   0.01862  -0.0380   0.7749   1.0000
  -2.500   0.1418   0.02770   0.01851  -0.0374   0.7594   1.0000
  -2.250   0.1648   0.02789   0.01848  -0.0373   0.7444   1.0000
  -2.000   0.1882   0.02813   0.01854  -0.0374   0.7307   1.0000
  -1.750   0.2113   0.02843   0.01865  -0.0373   0.7182   1.0000
  -1.500   0.2324   0.02873   0.01875  -0.0365   0.7075   1.0000
  -1.250   0.2563   0.02911   0.01900  -0.0368   0.6958   1.0000
  -1.000   0.2803   0.02959   0.01934  -0.0371   0.6854   1.0000
  -0.750   0.3018   0.02997   0.01957  -0.0364   0.6765   1.0000
  -0.500   0.3268   0.03061   0.02015  -0.0373   0.6661   1.0000
  -0.250   0.3476   0.03103   0.02041  -0.0362   0.6586   1.0000
   0.000   0.3732   0.03189   0.02127  -0.0376   0.6489   1.0000
   0.250   0.3941   0.03239   0.02164  -0.0366   0.6421   1.0000
   0.500   0.4184   0.03345   0.02271  -0.0380   0.6330   1.0000
   0.750   0.4396   0.03407   0.02325  -0.0373   0.6262   1.0000
   1.000   0.4621   0.03533   0.02454  -0.0385   0.6185   1.0000
   1.250   0.4830   0.03626   0.02544  -0.0384   0.6114   1.0000
   1.500   0.5032   0.03729   0.02645  -0.0381   0.6051   1.0000
   1.750   0.5221   0.03899   0.02821  -0.0393   0.5978   1.0000
   2.000   0.5416   0.03991   0.02910  -0.0384   0.5924   1.0000
   2.250   0.5567   0.04190   0.03115  -0.0392   0.5860   1.0000
   2.500   0.5700   0.04383   0.03314  -0.0394   0.5796   1.0000
   2.750   0.5887   0.04476   0.03405  -0.0381   0.5746   1.0000
   3.000   0.5923   0.04783   0.03721  -0.0387   0.5691   1.0000
   3.250   0.5933   0.05070   0.04014  -0.0385   0.5640   1.0000
   3.500   0.6021   0.05267   0.04213  -0.0375   0.5597   1.0000
   3.750   0.6163   0.05425   0.04370  -0.0362   0.5557   1.0000
   4.000   0.5952   0.05855   0.04805  -0.0351   0.5540   1.0000
   4.250   0.5762   0.06219   0.05169  -0.0331   0.5536   1.0000
   4.500   0.5642   0.06532   0.05482  -0.0311   0.5548   1.0000
   4.750   0.5589   0.06809   0.05759  -0.0291   0.5565   1.0000
   5.000   0.3497   0.07780   0.06724  -0.0206   0.7260   1.0000
   5.250   0.3514   0.07884   0.06826  -0.0181   0.7109   1.0000
   5.500   0.3534   0.08014   0.06955  -0.0159   0.6970   1.0000
   5.750   0.3604   0.08186   0.07125  -0.0143   0.6838   1.0000
   6.000   0.3788   0.08436   0.07377  -0.0143   0.6729   1.0000
   6.500   0.3920   0.08754   0.07695  -0.0111   0.6461   1.0000
   6.750   0.3969   0.08938   0.07878  -0.0096   0.6348   1.0000
   7.000   0.4326   0.09324   0.08269  -0.0113   0.6245   1.0000
   7.250   0.4205   0.09350   0.08294  -0.0078   0.6107   1.0000
   7.500   0.4198   0.09515   0.08461  -0.0059   0.6002   1.0000
   7.750   0.4541   0.09912   0.08864  -0.0072   0.5906   1.0000
   8.000   0.4407   0.09937   0.08887  -0.0040   0.5771   1.0000
   8.250   0.4415   0.10128   0.09079  -0.0025   0.5676   1.0000
   8.500   0.4653   0.10444   0.09401  -0.0027   0.5576   1.0000
   8.750   0.4542   0.10529   0.09486  -0.0003   0.5459   1.0000
   9.000   0.4726   0.10863   0.09827  -0.0002   0.5380   1.0000
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