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EPPLER 338 AIRFOIL (e338-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 338 AIRFOIL (e338-il)
Reynolds number: 50,000
Max Cl/Cd: 15.78 at α=0.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e338-il-50000.txt
Download as CSV file: xf-e338-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 338 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3419   0.11374   0.10742  -0.0205   1.0000   0.1941
  -9.250  -0.3261   0.11001   0.10373  -0.0194   1.0000   0.2050
  -9.000  -0.3297   0.10700   0.10085  -0.0203   1.0000   0.2120
  -8.750  -0.3325   0.10470   0.09864  -0.0205   1.0000   0.2240
  -8.500  -0.3173   0.10063   0.09464  -0.0193   1.0000   0.2359
  -8.250  -0.3182   0.09767   0.09180  -0.0191   1.0000   0.2476
  -8.000  -0.3491   0.09673   0.09107  -0.0203   1.0000   0.2584
  -7.750  -0.3441   0.09365   0.08811  -0.0188   1.0000   0.2747
  -7.500  -0.3458   0.09102   0.08561  -0.0172   1.0000   0.2912
  -7.250  -0.3130   0.08694   0.08156  -0.0139   1.0000   0.3201
  -6.750  -0.3222   0.08300   0.07798  -0.0081   1.0000   0.3728
  -6.500  -0.2831   0.07980   0.07483  -0.0032   1.0000   0.4349
  -6.250  -0.2461   0.07717   0.07225   0.0023   1.0000   0.5173
  -6.000  -0.2137   0.07511   0.07029   0.0073   1.0000   0.6068
  -5.750  -0.1255   0.06960   0.06473   0.0053   1.0000   0.7259
  -4.750  -0.1945   0.06365   0.05941  -0.0029   0.9481   0.6249
  -4.500  -0.2555   0.05903   0.05484  -0.0113   0.9190   0.5431
  -4.250  -0.3021   0.05354   0.04881  -0.0266   0.8913   0.4246
  -4.000  -0.2319   0.04681   0.03958  -0.0433   0.8759   0.1710
  -3.750  -0.1904   0.04367   0.03561  -0.0444   0.8631   0.1380
  -3.500  -0.1422   0.04061   0.03182  -0.0463   0.8528   0.1221
  -3.250  -0.1115   0.03857   0.02935  -0.0459   0.8386   0.1163
  -3.000  -0.0796   0.03696   0.02736  -0.0458   0.8251   0.1161
  -2.750   0.2753   0.02468   0.01730  -0.0889   0.8218   1.0000
  -2.500   0.2964   0.02497   0.01704  -0.0877   0.8055   1.0000
  -2.250   0.3165   0.02532   0.01699  -0.0866   0.7901   1.0000
  -2.000   0.3366   0.02574   0.01709  -0.0857   0.7759   1.0000
  -1.750   0.3563   0.02619   0.01726  -0.0847   0.7629   1.0000
  -1.500   0.3765   0.02660   0.01739  -0.0835   0.7514   1.0000
  -1.250   0.3954   0.02712   0.01769  -0.0824   0.7399   1.0000
  -1.000   0.4124   0.02782   0.01824  -0.0813   0.7288   1.0000
  -0.750   0.4330   0.02828   0.01846  -0.0801   0.7197   1.0000
  -0.500   0.4487   0.02912   0.01919  -0.0789   0.7091   1.0000
  -0.250   0.4664   0.02986   0.01979  -0.0778   0.7003   1.0000
   0.000   0.4832   0.03068   0.02049  -0.0766   0.6915   1.0000
   0.250   0.4986   0.03164   0.02136  -0.0753   0.6832   1.0000
   0.500   0.5141   0.03258   0.02220  -0.0740   0.6751   1.0000
   0.750   0.5284   0.03367   0.02321  -0.0726   0.6677   1.0000
   1.000   0.5389   0.03501   0.02451  -0.0711   0.6599   1.0000
   1.250   0.5592   0.03570   0.02508  -0.0698   0.6539   1.0000
   1.500   0.5556   0.03799   0.02741  -0.0675   0.6458   1.0000
   1.750   0.5744   0.03882   0.02816  -0.0662   0.6399   1.0000
   2.000   0.5682   0.04124   0.03060  -0.0635   0.6335   1.0000
   2.250   0.5642   0.04341   0.03275  -0.0607   0.6272   1.0000
   2.500   0.5911   0.04392   0.03317  -0.0600   0.6221   1.0000
   2.750   0.5512   0.04799   0.03729  -0.0546   0.6174   1.0000
   3.000   0.5181   0.05126   0.04056  -0.0493   0.6137   1.0000
   3.250   0.4859   0.05401   0.04328  -0.0435   0.6119   1.0000
   3.500   0.4628   0.05652   0.04576  -0.0390   0.6111   1.0000
   3.750   0.4423   0.05902   0.04823  -0.0351   0.6118   1.0000
   4.000   0.4254   0.06151   0.05068  -0.0319   0.6145   1.0000
   4.250   0.4211   0.06390   0.05304  -0.0302   0.6183   1.0000
   4.500   0.4340   0.06626   0.05536  -0.0300   0.6215   1.0000
   5.250   0.3039   0.07486   0.06403  -0.0207   0.7415   1.0000
   5.500   0.3136   0.07645   0.06557  -0.0196   0.7289   1.0000
   5.750   0.3421   0.07955   0.06862  -0.0211   0.7201   1.0000
   6.000   0.3505   0.08079   0.06982  -0.0199   0.7063   1.0000
   6.250   0.3545   0.08205   0.07105  -0.0182   0.6936   1.0000
   6.500   0.3674   0.08415   0.07313  -0.0178   0.6830   1.0000
   6.750   0.3958   0.08717   0.07614  -0.0191   0.6720   1.0000
   7.000   0.3935   0.08801   0.07696  -0.0170   0.6593   1.0000
   7.250   0.4027   0.09000   0.07895  -0.0163   0.6488   1.0000
   7.500   0.4351   0.09360   0.08256  -0.0180   0.6386   1.0000
   7.750   0.4290   0.09420   0.08315  -0.0158   0.6262   1.0000
   8.000   0.4372   0.09634   0.08530  -0.0152   0.6160   1.0000
   8.250   0.4673   0.09985   0.08884  -0.0166   0.6059   1.0000
   8.500   0.4614   0.10070   0.08970  -0.0148   0.5936   1.0000
   8.750   0.4731   0.10338   0.09241  -0.0148   0.5854   1.0000
   9.000   0.4954   0.10629   0.09536  -0.0153   0.5737   1.0000
   9.250   0.4905   0.10751   0.09659  -0.0140   0.5621   1.0000
   9.500   0.5171   0.11162   0.10075  -0.0152   0.5554   1.0000
   9.750   0.5172   0.11280   0.10196  -0.0142   0.5426   1.0000
  10.000   0.5178   0.11475   0.10394  -0.0137   0.5325   1.0000
  10.250   0.5502   0.11921   0.10851  -0.0151   0.5241   1.0000
  10.500   0.5383   0.11981   0.10913  -0.0138   0.5127   1.0000
  10.750   0.5528   0.12320   0.11257  -0.0143   0.5053   1.0000
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