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EPPLER 377 (MODIFIED) AIRFOIL (e377m-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 377 (MODIFIED) AIRFOIL (e377m-il)
Reynolds number: 1,000,000
Max Cl/Cd: 136.98 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e377m-il-1000000-n5.txt
Download as CSV file: xf-e377m-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 377 (MODIFIED) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.1759   0.09799   0.09515  -0.0246   0.6320   0.0049
  -7.750  -0.1679   0.09576   0.09289  -0.0252   0.6231   0.0050
  -7.500  -0.1602   0.09371   0.09083  -0.0258   0.6149   0.0050
  -7.250  -0.1490   0.09142   0.08851  -0.0274   0.6065   0.0051
  -7.000  -0.1362   0.08896   0.08604  -0.0293   0.6005   0.0051
  -6.750  -0.1226   0.08645   0.08350  -0.0313   0.5929   0.0051
  -6.500  -0.1078   0.08389   0.08093  -0.0335   0.5875   0.0051
  -6.250  -0.0920   0.08133   0.07834  -0.0357   0.5806   0.0051
  -6.000  -0.0750   0.07869   0.07568  -0.0383   0.5756   0.0051
  -5.750  -0.0568   0.07598   0.07294  -0.0409   0.5700   0.0051
  -5.500  -0.0377   0.07334   0.07027  -0.0436   0.5642   0.0051
  -5.250  -0.0177   0.07056   0.06747  -0.0464   0.5594   0.0051
  -5.000   0.0019   0.06801   0.06489  -0.0490   0.5544   0.0048
  -4.750   0.0249   0.06532   0.06217  -0.0522   0.5497   0.0043
  -4.500   0.0497   0.06248   0.05930  -0.0557   0.5451   0.0040
  -4.250   0.0762   0.05957   0.05635  -0.0593   0.5401   0.0039
  -4.000   0.1044   0.05665   0.05338  -0.0632   0.5359   0.0040
  -3.750   0.1344   0.05365   0.05034  -0.0672   0.5318   0.0044
  -3.500   0.1710   0.04959   0.04621  -0.0727   0.5278   0.0053
  -3.000   0.2254   0.04642   0.04295  -0.0775   0.5188   0.0067
  -2.750   0.2588   0.04382   0.04029  -0.0812   0.5147   0.0070
  -2.500   0.2937   0.04114   0.03753  -0.0850   0.5106   0.0069
  -2.250   0.3330   0.03797   0.03426  -0.0895   0.5069   0.0078
  -2.000   0.3672   0.03578   0.03200  -0.0926   0.5028   0.0089
  -1.750   0.3966   0.03452   0.03068  -0.0944   0.4983   0.0098
  -1.500   0.4297   0.03279   0.02887  -0.0968   0.4945   0.0113
  -1.250   0.4659   0.03049   0.02648  -0.0998   0.4909   0.0102
  -1.000   0.5025   0.02823   0.02412  -0.1025   0.4867   0.0099
  -0.750   0.5377   0.02628   0.02205  -0.1047   0.4824   0.0106
  -0.500   0.5730   0.02435   0.02000  -0.1067   0.4789   0.0116
  -0.250   0.6069   0.02262   0.01816  -0.1083   0.4753   0.0121
   0.000   0.6395   0.02114   0.01658  -0.1095   0.4710   0.0125
   0.250   0.6750   0.01893   0.01418  -0.1111   0.4669   0.0122
   0.500   0.7221   0.01217   0.00660  -0.1144   0.4642   0.0123
   0.750   0.7511   0.01105   0.00526  -0.1146   0.4604   0.0127
   1.000   0.7792   0.01030   0.00432  -0.1146   0.4561   0.0134
   1.250   0.8068   0.00993   0.00383  -0.1144   0.4517   0.0147
   1.500   0.8344   0.00966   0.00349  -0.1142   0.4480   0.0156
   1.750   0.8618   0.00942   0.00320  -0.1141   0.4439   0.0164
   2.000   0.8889   0.00919   0.00290  -0.1139   0.4394   0.0178
   2.250   0.9160   0.00893   0.00258  -0.1137   0.4354   0.0191
   2.500   0.9427   0.00850   0.00214  -0.1135   0.4312   0.0281
   2.750   0.9689   0.00818   0.00185  -0.1133   0.4264   0.0561
   3.000   0.9958   0.00822   0.00191  -0.1131   0.4216   0.0720
   3.250   1.0229   0.00828   0.00197  -0.1128   0.4160   0.0771
   3.500   1.0498   0.00843   0.00211  -0.1126   0.4093   0.0822
   3.750   1.0769   0.00853   0.00222  -0.1124   0.4028   0.0855
   4.000   1.1036   0.00864   0.00230  -0.1122   0.3954   0.0879
   4.250   1.1305   0.00872   0.00240  -0.1120   0.3889   0.0893
   4.500   1.1572   0.00886   0.00252  -0.1118   0.3816   0.0909
   4.750   1.1839   0.00893   0.00259  -0.1116   0.3748   0.0924
   5.250   1.2368   0.00913   0.00278  -0.1111   0.3576   0.0954
   5.500   1.2630   0.00927   0.00289  -0.1109   0.3482   0.0966
   5.750   1.2891   0.00944   0.00304  -0.1107   0.3371   0.0974
   6.000   1.3150   0.00960   0.00320  -0.1105   0.3246   0.0990
   6.250   1.3407   0.00983   0.00340  -0.1102   0.3094   0.1002
   6.500   1.3660   0.01012   0.00363  -0.1099   0.2904   0.1013
   6.750   1.3909   0.01046   0.00390  -0.1096   0.2701   0.1025
   7.000   1.4148   0.01095   0.00427  -0.1092   0.2412   0.1039
   7.250   1.4354   0.01196   0.00494  -0.1086   0.1831   0.1052
   7.500   1.4550   0.01309   0.00574  -0.1078   0.1253   0.1066
   7.750   1.4758   0.01396   0.00640  -0.1071   0.0899   0.1078
   8.000   1.4970   0.01471   0.00701  -0.1064   0.0642   0.1088
   8.250   1.5177   0.01548   0.00766  -0.1057   0.0427   0.1102
   8.500   1.5369   0.01641   0.00846  -0.1048   0.0203   0.1121
   8.750   1.5538   0.01757   0.00953  -0.1035   0.0031   0.1133
   9.000   1.5748   0.01815   0.01021  -0.1027   0.0020   0.1148
   9.250   1.5960   0.01866   0.01079  -0.1020   0.0019   0.1164
   9.500   1.6164   0.01922   0.01142  -0.1011   0.0017   0.1180
   9.750   1.6359   0.01982   0.01209  -0.1002   0.0016   0.1196
  10.000   1.6544   0.02048   0.01283  -0.0991   0.0015   0.1209
  10.250   1.6714   0.02121   0.01365  -0.0978   0.0013   0.1224
  10.500   1.6869   0.02202   0.01454  -0.0964   0.0012   0.1242
  10.750   1.6997   0.02295   0.01559  -0.0946   0.0011   0.1259
  11.000   1.7064   0.02410   0.01685  -0.0920   0.0010   0.1277
  11.250   1.7026   0.02553   0.01842  -0.0880   0.0009   0.1289
  11.500   1.6959   0.02747   0.02050  -0.0845   0.0008   0.1298
  11.750   1.6965   0.02921   0.02234  -0.0824   0.0008   0.1312
  12.000   1.6985   0.03109   0.02431  -0.0809   0.0008   0.1322
  12.250   1.6979   0.03343   0.02677  -0.0797   0.0008   0.1329
  12.500   1.6964   0.03607   0.02952  -0.0788   0.0008   0.1343
  12.750   1.6948   0.03892   0.03249  -0.0782   0.0007   0.1353
  13.000   1.6910   0.04217   0.03586  -0.0779   0.0007   0.1368
  13.250   1.6880   0.04546   0.03927  -0.0778   0.0007   0.1381
  13.500   1.6825   0.04919   0.04312  -0.0778   0.0007   0.1392
  13.750   1.6767   0.05306   0.04711  -0.0780   0.0007   0.1402
  14.000   1.6698   0.05720   0.05137  -0.0785   0.0007   0.1415
  14.250   1.6629   0.06141   0.05569  -0.0790   0.0007   0.1425
  14.500   1.6538   0.06612   0.06054  -0.0799   0.0007   0.1433
  14.750   1.6459   0.07084   0.06540  -0.0809   0.0007   0.1441
  15.000   1.6383   0.07568   0.07036  -0.0821   0.0007   0.1454
  15.250   1.6293   0.08092   0.07573  -0.0835   0.0007   0.1468
  15.500   1.6212   0.08615   0.08108  -0.0851   0.0007   0.1484
  15.750   1.6124   0.09165   0.08671  -0.0869   0.0007   0.1500
  16.000   1.6038   0.09728   0.09246  -0.0888   0.0007   0.1516
  16.250   1.5948   0.10305   0.09837  -0.0909   0.0007   0.1532
  16.500   1.5860   0.10896   0.10440  -0.0932   0.0007   0.1545
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