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EPPLER 908 AIRFOIL (e908-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 908 AIRFOIL (e908-il)
Reynolds number: 1,000,000
Max Cl/Cd: 117.89 at α=1°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e908-il-1000000-n5.txt
Download as CSV file: xf-e908-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2776   0.07247   0.07070  -0.0962   0.9715   0.0021
  -8.500  -0.2730   0.06638   0.06463  -0.1027   0.9700   0.0019
  -8.250  -0.2773   0.06179   0.06005  -0.1057   0.9625   0.0019
  -8.000  -0.2683   0.05426   0.05248  -0.1180   0.9588   0.0020
  -7.750  -0.2620   0.04693   0.04504  -0.1257   0.9543   0.0019
  -7.500  -0.2545   0.04061   0.03853  -0.1296   0.9499   0.0018
  -7.250  -0.2423   0.03437   0.03199  -0.1326   0.9469   0.0016
  -7.000  -0.2306   0.02926   0.02651  -0.1332   0.9435   0.0015
  -6.750  -0.2232   0.02455   0.02140  -0.1314   0.9386   0.0013
  -6.500  -0.2089   0.01961   0.01591  -0.1300   0.9355   0.0011
  -6.250  -0.1911   0.01468   0.01030  -0.1283   0.9332   0.0009
  -6.000  -0.1704   0.01231   0.00757  -0.1270   0.9312   0.0009
  -5.750  -0.1495   0.01110   0.00616  -0.1258   0.9289   0.0009
  -5.500  -0.1263   0.01027   0.00519  -0.1251   0.9269   0.0010
  -5.250  -0.1014   0.00965   0.00447  -0.1248   0.9252   0.0012
  -5.000  -0.0753   0.00918   0.00391  -0.1247   0.9235   0.0015
  -4.750  -0.0480   0.00880   0.00346  -0.1249   0.9221   0.0019
  -4.500  -0.0199   0.00850   0.00309  -0.1252   0.9208   0.0023
  -4.250   0.0088   0.00831   0.00286  -0.1257   0.9193   0.0026
  -3.750   0.0580   0.00769   0.00210  -0.1247   0.9137   0.0076
  -3.500   0.0849   0.00745   0.00180  -0.1246   0.9111   0.0149
  -3.250   0.1123   0.00704   0.00155  -0.1249   0.9086   0.0688
  -2.750   0.1655   0.00654   0.00132  -0.1251   0.9042   0.1612
  -2.500   0.1916   0.00639   0.00124  -0.1250   0.9018   0.1886
  -2.250   0.2165   0.00590   0.00112  -0.1249   0.8996   0.3144
  -2.000   0.2435   0.00568   0.00105  -0.1251   0.8976   0.3726
  -1.750   0.2713   0.00546   0.00098  -0.1254   0.8958   0.4351
  -1.500   0.2998   0.00525   0.00093  -0.1259   0.8941   0.4978
  -1.250   0.3252   0.00506   0.00094  -0.1256   0.8918   0.5610
  -1.000   0.3512   0.00498   0.00097  -0.1255   0.8892   0.6037
  -0.750   0.3783   0.00495   0.00099  -0.1254   0.8867   0.6264
  -0.500   0.4060   0.00493   0.00099  -0.1256   0.8844   0.6409
  -0.250   0.4349   0.00492   0.00100  -0.1260   0.8822   0.6515
   0.000   0.4627   0.00490   0.00103  -0.1261   0.8797   0.6651
   0.250   0.4883   0.00488   0.00108  -0.1258   0.8765   0.6816
   0.500   0.5149   0.00486   0.00113  -0.1257   0.8731   0.6969
   0.750   0.5428   0.00485   0.00119  -0.1258   0.8700   0.7100
   1.000   0.5706   0.00484   0.00123  -0.1259   0.8668   0.7210
   1.500   0.5704   0.00609   0.00131  -0.1130   0.5940   0.7387
   2.000   0.5653   0.00965   0.00251  -0.1014   0.0027   0.7540
   2.250   0.5902   0.00978   0.00266  -0.1010   0.0019   0.7604
   2.500   0.6150   0.00994   0.00285  -0.1005   0.0015   0.7675
   2.750   0.6394   0.01013   0.00311  -0.0999   0.0014   0.7743
   3.000   0.6633   0.01037   0.00350  -0.0991   0.0014   0.7821
   3.250   0.6860   0.01071   0.00395  -0.0980   0.0014   0.7901
   3.500   0.7072   0.01121   0.00459  -0.0965   0.0014   0.7994
   4.250   0.7628   0.01390   0.00773  -0.0902   0.0018   0.8371
   4.500   0.7887   0.01564   0.00965  -0.0894   0.0021   0.8523
   5.500   0.9037   0.02367   0.01858  -0.0881   0.0036   1.0000
   5.750   0.9238   0.02647   0.02169  -0.0863   0.0034   1.0000
   6.000   0.9291   0.03327   0.02904  -0.0814   0.0030   1.0000
   6.250   0.9416   0.03610   0.03213  -0.0783   0.0030   1.0000
   6.500   0.9519   0.03905   0.03532  -0.0751   0.0030   1.0000
   6.750   0.9604   0.04216   0.03867  -0.0716   0.0030   1.0000
   7.000   0.9672   0.04533   0.04207  -0.0680   0.0030   1.0000
   7.250   0.9721   0.04860   0.04555  -0.0644   0.0030   1.0000
   7.500   0.9748   0.05199   0.04914  -0.0607   0.0030   1.0000
   7.750   0.9755   0.05535   0.05270  -0.0570   0.0030   1.0000
   8.000   0.9737   0.05879   0.05630  -0.0533   0.0030   1.0000
   8.250   0.9691   0.06218   0.05985  -0.0495   0.0030   1.0000
   8.500   0.9598   0.06531   0.06312  -0.0452   0.0030   1.0000
   8.750   0.9462   0.06813   0.06605  -0.0406   0.0030   1.0000
   9.000   0.9312   0.07119   0.06922  -0.0367   0.0030   1.0000
   9.250   0.9155   0.07448   0.07261  -0.0338   0.0030   1.0000
   9.500   0.8987   0.07827   0.07650  -0.0318   0.0030   1.0000
   9.750   0.8817   0.08250   0.08082  -0.0310   0.0030   1.0000
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