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EPPLER 908 AIRFOIL (e908-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 908 AIRFOIL (e908-il)
Reynolds number: 100,000
Max Cl/Cd: 41.24 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e908-il-100000-n5.txt
Download as CSV file: xf-e908-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 908 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4885   0.09607   0.09151  -0.0297   1.0000   0.0120
  -7.750  -0.4976   0.09287   0.08839  -0.0293   1.0000   0.0119
  -7.500  -0.5088   0.08986   0.08545  -0.0286   1.0000   0.0116
  -7.250  -0.5225   0.08711   0.08277  -0.0276   1.0000   0.0115
  -7.000  -0.5332   0.08360   0.07932  -0.0283   1.0000   0.0112
  -6.750  -0.5399   0.07901   0.07477  -0.0308   1.0000   0.0110
  -6.500  -0.5412   0.07382   0.06955  -0.0338   0.9995   0.0106
  -6.250  -0.5266   0.06659   0.06218  -0.0409   0.9956   0.0100
  -6.000  -0.5099   0.05935   0.05470  -0.0464   0.9919   0.0095
  -5.750  -0.4914   0.05262   0.04760  -0.0504   0.9884   0.0090
  -5.500  -0.4699   0.04728   0.04185  -0.0535   0.9854   0.0091
  -5.250  -0.4462   0.04433   0.03849  -0.0563   0.9829   0.0119
  -5.000  -0.4214   0.04031   0.03395  -0.0579   0.9803   0.0137
  -4.750  -0.3944   0.03691   0.02993  -0.0588   0.9776   0.0156
  -4.500  -0.3658   0.03370   0.02610  -0.0597   0.9753   0.0161
  -4.250  -0.3354   0.03062   0.02240  -0.0604   0.9735   0.0161
  -4.000  -0.3040   0.02822   0.01949  -0.0610   0.9718   0.0165
  -3.750  -0.2721   0.02636   0.01725  -0.0617   0.9703   0.0170
  -3.500  -0.2449   0.02485   0.01554  -0.0614   0.9677   0.0175
  -3.250  -0.2180   0.02305   0.01355  -0.0615   0.9652   0.0192
  -3.000  -0.1885   0.02205   0.01238  -0.0620   0.9624   0.0251
  -2.750  -0.1570   0.02112   0.01127  -0.0628   0.9601   0.0401
  -2.500  -0.1268   0.01948   0.01059  -0.0643   0.9584   0.2534
  -2.250  -0.1106   0.01811   0.01102  -0.0621   0.9554   0.6625
  -2.000  -0.0859   0.01811   0.01086  -0.0612   0.9510   0.7160
  -1.750  -0.0579   0.01817   0.01079  -0.0610   0.9476   0.7548
  -1.500  -0.0282   0.01826   0.01073  -0.0612   0.9448   0.7887
  -1.250  -0.0075   0.01821   0.01061  -0.0597   0.9392   0.8161
  -1.000   0.0197   0.01822   0.01054  -0.0594   0.9353   0.8475
  -0.750   0.0506   0.01822   0.01040  -0.0597   0.9326   0.8877
  -0.500   0.0904   0.01806   0.01024  -0.0624   0.9283   1.0000
  -0.250   0.1211   0.01816   0.01020  -0.0637   0.9237   1.0000
   0.000   0.1560   0.01831   0.01022  -0.0657   0.9207   1.0000
   0.250   0.1825   0.01842   0.01024  -0.0660   0.9151   1.0000
   0.500   0.2132   0.01855   0.01031  -0.0672   0.9105   1.0000
   0.750   0.2483   0.01870   0.01039  -0.0691   0.9075   1.0000
   1.000   0.2721   0.01883   0.01050  -0.0688   0.9008   1.0000
   1.250   0.3042   0.01897   0.01062  -0.0701   0.8965   1.0000
   1.500   0.3400   0.01909   0.01076  -0.0721   0.8938   1.0000
   1.750   0.3609   0.01926   0.01096  -0.0712   0.8856   1.0000
   2.000   0.3951   0.01937   0.01121  -0.0728   0.8821   1.0000
   2.250   0.4182   0.01954   0.01146  -0.0723   0.8744   1.0000
   2.500   0.4507   0.01965   0.01167  -0.0735   0.8701   1.0000
   2.750   0.4757   0.01982   0.01196  -0.0733   0.8628   1.0000
   3.000   0.5069   0.01992   0.01221  -0.0742   0.8575   1.0000
   3.250   0.5322   0.02007   0.01254  -0.0739   0.8497   1.0000
   3.500   0.5646   0.02010   0.01282  -0.0748   0.8440   1.0000
   3.750   0.6599   0.01600   0.00672  -0.0782   0.2979   1.0000
   4.000   0.6659   0.01913   0.00823  -0.0749   0.0222   1.0000
   4.250   0.6830   0.02034   0.00963  -0.0726   0.0177   1.0000
   4.500   0.7010   0.02133   0.01083  -0.0705   0.0152   1.0000
   4.750   0.7192   0.02231   0.01193  -0.0688   0.0112   1.0000
   5.000   0.7368   0.02397   0.01367  -0.0672   0.0085   1.0000
   5.250   0.7679   0.02679   0.01658  -0.0676   0.0080   1.0000
   5.500   0.8046   0.02939   0.01940  -0.0688   0.0078   1.0000
   5.750   0.8387   0.03232   0.02264  -0.0695   0.0078   1.0000
   6.000   0.8666   0.03550   0.02619  -0.0690   0.0079   1.0000
   6.500   0.9079   0.04087   0.03250  -0.0659   0.0082   1.0000
   6.750   0.9251   0.04322   0.03520  -0.0637   0.0084   1.0000
   7.000   0.9407   0.04568   0.03805  -0.0612   0.0088   1.0000
   7.250   0.9541   0.04869   0.04150  -0.0582   0.0094   1.0000
   7.500   0.9624   0.05247   0.04575  -0.0545   0.0101   1.0000
   7.750   0.9666   0.05627   0.04994  -0.0508   0.0109   1.0000
   8.000   0.9669   0.06003   0.05403  -0.0471   0.0115   1.0000
   8.250   0.9639   0.06371   0.05799  -0.0435   0.0121   1.0000
   8.500   0.9573   0.06730   0.06183  -0.0399   0.0126   1.0000
   8.750   0.9466   0.07056   0.06527  -0.0360   0.0130   1.0000
   9.000   0.9332   0.07389   0.06878  -0.0325   0.0134   1.0000
   9.250   0.9190   0.07731   0.07235  -0.0298   0.0136   1.0000
   9.500   0.9027   0.08115   0.07632  -0.0279   0.0139   1.0000
   9.750   0.8859   0.08535   0.08065  -0.0270   0.0141   1.0000
  10.000   0.8698   0.08995   0.08535  -0.0275   0.0141   1.0000
  10.250   0.8539   0.09532   0.09080  -0.0293   0.0142   1.0000
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