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EPPLER 908 AIRFOIL (e908-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 908 AIRFOIL (e908-il)
Reynolds number: 1,000,000
Max Cl/Cd: 137.03 at α=1.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e908-il-1000000.txt
Download as CSV file: xf-e908-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2238   0.08109   0.07946  -0.0816   0.9831   0.0057
  -9.500  -0.2197   0.07654   0.07491  -0.0838   0.9826   0.0057
  -7.250  -0.2669   0.04605   0.04414  -0.1173   0.9617   0.0056
  -7.000  -0.2496   0.04077   0.03865  -0.1210   0.9603   0.0057
  -6.750  -0.2303   0.03600   0.03362  -0.1240   0.9593   0.0058
  -6.500  -0.2090   0.03150   0.02880  -0.1264   0.9585   0.0058
  -6.250  -0.2148   0.02969   0.02682  -0.1209   0.9515   0.0058
  -6.000  -0.1944   0.02612   0.02288  -0.1213   0.9499   0.0058
  -5.750  -0.1773   0.01917   0.01524  -0.1214   0.9484   0.0051
  -4.250  -0.0256   0.01086   0.00590  -0.1200   0.9396   0.0096
  -4.000   0.0024   0.00979   0.00467  -0.1199   0.9380   0.0077
  -3.750   0.0330   0.00919   0.00396  -0.1206   0.9369   0.0072
  -3.500   0.0647   0.00859   0.00319  -0.1215   0.9358   0.0076
  -3.250   0.0958   0.00785   0.00252  -0.1223   0.9348   0.0669
  -3.000   0.1262   0.00719   0.00230  -0.1235   0.9338   0.1939
  -2.750   0.1564   0.00671   0.00215  -0.1247   0.9327   0.3016
  -2.500   0.1726   0.00631   0.00214  -0.1226   0.9291   0.4241
  -2.250   0.1954   0.00574   0.00215  -0.1220   0.9267   0.6231
  -2.000   0.2247   0.00567   0.00207  -0.1225   0.9251   0.6491
  -1.750   0.2554   0.00560   0.00201  -0.1232   0.9238   0.6647
  -1.500   0.2867   0.00555   0.00195  -0.1242   0.9225   0.6772
  -1.000   0.3499   0.00547   0.00188  -0.1262   0.9201   0.6988
  -0.750   0.3726   0.00549   0.00193  -0.1251   0.9170   0.7062
  -0.500   0.3987   0.00548   0.00193  -0.1249   0.9143   0.7136
  -0.250   0.4277   0.00544   0.00191  -0.1252   0.9122   0.7212
   0.000   0.4582   0.00539   0.00189  -0.1260   0.9103   0.7308
   0.250   0.4895   0.00534   0.00188  -0.1269   0.9085   0.7420
   0.500   0.5187   0.00532   0.00192  -0.1273   0.9063   0.7545
   0.750   0.5416   0.00531   0.00201  -0.1263   0.9024   0.7655
   1.000   0.5697   0.00527   0.00203  -0.1264   0.8992   0.7756
   1.250   0.6006   0.00521   0.00201  -0.1272   0.8962   0.7847
   1.500   0.6263   0.00506   0.00190  -0.1265   0.8866   0.7933
   1.750   0.6454   0.00471   0.00146  -0.1239   0.8431   0.8014
   2.000   0.6499   0.00518   0.00139  -0.1182   0.7175   0.8110
   2.250   0.6323   0.00667   0.00186  -0.1085   0.4874   0.8240
   2.500   0.6204   0.00910   0.00271  -0.1011   0.1016   0.8392
   2.750   0.6375   0.00981   0.00319  -0.0989   0.0083   0.8549
   3.000   0.6594   0.01006   0.00362  -0.0976   0.0074   0.8751
   3.250   0.6786   0.01024   0.00394  -0.0957   0.0062   0.9082
   3.500   0.7042   0.01050   0.00438  -0.0952   0.0055   1.0000
   3.750   0.7266   0.01096   0.00485  -0.0942   0.0041   1.0000
   4.000   0.7460   0.01170   0.00569  -0.0924   0.0036   1.0000
   4.250   0.7633   0.01276   0.00686  -0.0900   0.0037   1.0000
   5.250   0.8659   0.01205   0.00723  -0.0855   0.0058   1.0000
   5.500   0.8892   0.01328   0.00862  -0.0843   0.0050   1.0000
   5.750   0.9101   0.01523   0.01079  -0.0826   0.0046   1.0000
   6.000   0.9280   0.01750   0.01329  -0.0805   0.0042   1.0000
   6.250   0.9437   0.01999   0.01601  -0.0781   0.0039   1.0000
   6.500   0.9566   0.02278   0.01904  -0.0753   0.0037   1.0000
   6.750   0.9675   0.02570   0.02217  -0.0725   0.0035   1.0000
   7.000   0.9758   0.02885   0.02553  -0.0694   0.0034   1.0000
   7.250   0.9819   0.03217   0.02906  -0.0662   0.0032   1.0000
   7.500   0.9856   0.03564   0.03271  -0.0629   0.0032   1.0000
   7.750   0.9860   0.03936   0.03662  -0.0593   0.0031   1.0000
   8.000   0.9831   0.04325   0.04069  -0.0554   0.0030   1.0000
   8.250   0.9768   0.04723   0.04485  -0.0513   0.0030   1.0000
   8.500   0.9653   0.05090   0.04867  -0.0467   0.0029   1.0000
   8.750   0.9487   0.05411   0.05201  -0.0416   0.0029   1.0000
   9.000   0.9303   0.05755   0.05558  -0.0372   0.0029   1.0000
   9.250   0.9103   0.06141   0.05956  -0.0336   0.0029   1.0000
   9.500   0.8889   0.06576   0.06403  -0.0310   0.0029   1.0000
   9.750   0.8664   0.07074   0.06913  -0.0295   0.0029   1.0000
  10.000   0.8428   0.07646   0.07496  -0.0295   0.0030   1.0000
  10.250   0.8181   0.08320   0.08180  -0.0312   0.0030   1.0000
  10.500   0.7910   0.09218   0.09089  -0.0357   0.0031   1.0000
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