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EPPLER 377 AIRFOIL (e377-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 377 AIRFOIL (e377-il)
Reynolds number: 100,000
Max Cl/Cd: 104.73 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e377-il-100000.txt
Download as CSV file: xf-e377-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 377 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2232   0.11746   0.11301  -0.0177   1.0000   0.0272
  -8.250  -0.2185   0.11707   0.11272  -0.0191   1.0000   0.0273
  -8.000  -0.2125   0.11650   0.11225  -0.0209   1.0000   0.0273
  -7.500  -0.1938   0.10607   0.10196  -0.0207   1.0000   0.0279
  -7.250  -0.1855   0.10111   0.09707  -0.0200   1.0000   0.0286
  -7.000  -0.1822   0.09879   0.09487  -0.0195   1.0000   0.0292
  -6.500  -0.1666   0.09493   0.09121  -0.0235   0.9844   0.0304
  -6.250  -0.1285   0.09049   0.08674  -0.0319   0.9711   0.0320
  -6.000  -0.0875   0.08621   0.08242  -0.0409   0.9567   0.0338
  -5.750  -0.0454   0.08281   0.07895  -0.0503   0.9409   0.0362
  -5.500   0.0175   0.08462   0.08060  -0.0678   0.9151   0.0378
  -5.250   0.0388   0.07990   0.07585  -0.0705   0.8985   0.0383
  -5.000   0.0431   0.07386   0.06980  -0.0668   0.8836   0.0393
  -4.750   0.0587   0.07080   0.06669  -0.0675   0.8675   0.0407
  -4.500   0.0784   0.06835   0.06414  -0.0695   0.8522   0.0425
  -4.250   0.1001   0.06612   0.06183  -0.0720   0.8381   0.0447
  -4.000   0.1255   0.06410   0.05972  -0.0753   0.8256   0.0471
  -3.750   0.1762   0.06473   0.06016  -0.0854   0.8122   0.0497
  -3.500   0.2182   0.06368   0.05897  -0.0928   0.8002   0.0503
  -3.250   0.2191   0.05813   0.05347  -0.0891   0.7909   0.0513
  -3.000   0.2354   0.05497   0.05024  -0.0889   0.7826   0.0533
  -2.750   0.2622   0.05277   0.04797  -0.0915   0.7721   0.0573
  -2.500   0.3382   0.05484   0.04966  -0.1049   0.7617   0.0632
  -2.250   0.3439   0.04944   0.04431  -0.1026   0.7548   0.0644
  -2.000   0.3636   0.04652   0.04140  -0.1030   0.7459   0.0671
  -1.750   0.3956   0.04459   0.03931  -0.1057   0.7389   0.0717
  -1.500   0.4557   0.04476   0.03920  -0.1140   0.7295   0.0770
  -1.250   0.4704   0.04111   0.03555  -0.1133   0.7230   0.0793
  -1.000   0.5006   0.03933   0.03370  -0.1152   0.7149   0.0846
  -0.750   0.5056   0.01954   0.01422  -0.1086   0.6936   0.0942
  -0.500   0.5498   0.01908   0.01353  -0.1131   0.6863   0.1042
  -0.250   0.5722   0.01700   0.01139  -0.1134   0.6810   0.1091
   0.000   0.6109   0.01631   0.01054  -0.1167   0.6739   0.1184
   0.250   0.6471   0.01576   0.00974  -0.1186   0.6687   0.1305
   0.500   0.6718   0.01427   0.00830  -0.1197   0.6619   0.1363
   0.750   0.7037   0.01349   0.00736  -0.1210   0.6560   0.1491
   1.000   0.7353   0.01299   0.00670  -0.1224   0.6505   0.1724
   1.250   0.7645   0.01237   0.00601  -0.1233   0.6438   0.1908
   1.500   0.7946   0.01159   0.00503  -0.1237   0.6393   0.2152
   1.750   0.8238   0.01145   0.00485  -0.1249   0.6318   0.2529
   2.000   0.8479   0.01027   0.00361  -0.1248   0.6269   0.3609
   2.250   0.8763   0.00960   0.00286  -0.1254   0.6207   0.4178
   2.500   0.9256   0.01023   0.00257  -0.1270   0.6151   0.1833
   2.750   0.9538   0.00977   0.00183  -0.1265   0.6109   0.1829
   3.000   0.9791   0.01011   0.00219  -0.1269   0.6032   0.1881
   3.250   1.0057   0.01005   0.00200  -0.1264   0.5982   0.2043
   3.500   1.0316   0.01045   0.00234  -0.1265   0.5915   0.2144
   3.750   1.0575   0.01057   0.00239  -0.1261   0.5854   0.2283
   4.000   1.0821   0.01068   0.00250  -0.1255   0.5801   0.2533
   4.250   1.1050   0.01118   0.00307  -0.1252   0.5723   0.2781
   4.500   1.1300   0.01083   0.00269  -0.1240   0.5679   0.3141
   4.750   1.1509   0.01164   0.00370  -0.1239   0.5589   0.3525
   5.000   1.1792   0.01126   0.00388  -0.1235   0.5546   1.0000
   5.250   1.2011   0.01231   0.00497  -0.1231   0.5458   1.0000
   5.500   1.2269   0.01227   0.00479  -0.1220   0.5402   1.0000
   5.750   1.2476   0.01330   0.00592  -0.1216   0.5310   1.0000
   6.000   1.2747   0.01304   0.00557  -0.1204   0.5255   1.0000
   6.250   1.3504   0.02777   0.01983  -0.1272   0.5270   1.0000
   6.500   1.3727   0.02840   0.02064  -0.1265   0.5179   1.0000
   6.750   1.4001   0.02813   0.02033  -0.1254   0.5113   1.0000
   7.000   1.4217   0.02871   0.02109  -0.1246   0.5009   1.0000
   7.250   1.4461   0.02878   0.02124  -0.1236   0.4920   1.0000
   7.500   1.4729   0.02840   0.02087  -0.1224   0.4831   1.0000
   7.750   1.4954   0.02856   0.02126  -0.1214   0.4715   1.0000
   8.000   1.5190   0.02848   0.02132  -0.1202   0.4599   1.0000
   8.250   1.5434   0.02817   0.02113  -0.1190   0.4477   1.0000
   8.500   1.5677   0.02778   0.02086  -0.1177   0.4342   1.0000
   8.750   1.5910   0.02742   0.02062  -0.1163   0.4190   1.0000
   9.000   1.6137   0.02703   0.02043  -0.1149   0.4019   1.0000
   9.250   1.6362   0.02659   0.02006  -0.1134   0.3827   1.0000
   9.500   1.6537   0.02665   0.02035  -0.1116   0.3578   1.0000
   9.750   1.6693   0.02685   0.02064  -0.1096   0.3277   1.0000
  10.000   1.6791   0.02765   0.02144  -0.1073   0.2876   1.0000
  10.250   1.6814   0.02923   0.02279  -0.1046   0.2438   1.0000
  10.500   1.6777   0.03144   0.02478  -0.1016   0.2056   1.0000
  10.750   1.6692   0.03388   0.02707  -0.0983   0.1779   1.0000
  11.000   1.6570   0.03650   0.02966  -0.0952   0.1573   1.0000
  11.250   1.6441   0.03968   0.03279  -0.0931   0.1386   1.0000
  11.500   1.6313   0.04335   0.03643  -0.0920   0.1231   1.0000
  11.750   1.6182   0.04748   0.04053  -0.0914   0.1088   1.0000
  12.000   1.6043   0.05202   0.04506  -0.0911   0.0947   1.0000
  12.250   1.5883   0.05710   0.05014  -0.0912   0.0797   1.0000
  12.500   1.5698   0.06272   0.05571  -0.0914   0.0661   1.0000
  12.750   1.5516   0.06844   0.06136  -0.0917   0.0554   1.0000
  13.000   1.5357   0.07388   0.06672  -0.0919   0.0478   1.0000
  13.250   1.5287   0.07821   0.07116  -0.0914   0.0412   1.0000
  13.500   1.5227   0.08212   0.07492  -0.0904   0.0365   1.0000
  13.750   1.5227   0.08578   0.07884  -0.0901   0.0332   1.0000
  14.000   1.5208   0.08966   0.08283  -0.0902   0.0303   1.0000
  14.250   1.5212   0.09307   0.08624  -0.0896   0.0278   1.0000
  14.500   1.5298   0.09584   0.08917  -0.0872   0.0263   1.0000
  14.750   1.5302   0.10002   0.09364  -0.0871   0.0258   1.0000
  15.000   1.5271   0.10485   0.09876  -0.0876   0.0254   1.0000
  15.250   1.5205   0.11029   0.10449  -0.0890   0.0252   1.0000
  15.500   1.5107   0.11635   0.11082  -0.0911   0.0251   1.0000
  15.750   1.4990   0.12285   0.11759  -0.0939   0.0251   1.0000
  16.000   1.4856   0.12989   0.12489  -0.0975   0.0252   1.0000
  16.250   1.4715   0.13736   0.13259  -0.1017   0.0253   1.0000
  16.500   1.4565   0.14531   0.14076  -0.1066   0.0255   1.0000
  16.750   1.4414   0.15363   0.14928  -0.1120   0.0257   1.0000
  17.000   1.4259   0.16256   0.15839  -0.1180   0.0260   1.0000
  17.250   1.4103   0.17208   0.16805  -0.1246   0.0263   1.0000
  17.500   1.3959   0.18183   0.17790  -0.1314   0.0266   1.0000
  17.750   1.3832   0.19181   0.18800  -0.1383   0.0270   1.0000
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