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EPPLER 377 AIRFOIL (e377-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 377 AIRFOIL (e377-il)
Reynolds number: 50,000
Max Cl/Cd: 38.29 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e377-il-50000-n5.txt
Download as CSV file: xf-e377-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.1914   0.11120   0.10543  -0.0236   1.0000   0.0416
  -7.000  -0.1842   0.11088   0.10526  -0.0260   1.0000   0.0417
  -6.750  -0.1821   0.11074   0.10534  -0.0272   1.0000   0.0418
  -6.500  -0.1734   0.10068   0.09532  -0.0237   0.9892   0.0428
  -6.250  -0.1469   0.09518   0.08982  -0.0279   0.9688   0.0444
  -6.000  -0.1183   0.09125   0.08585  -0.0335   0.9479   0.0463
  -5.750  -0.0858   0.08755   0.08210  -0.0401   0.9272   0.0486
  -5.500  -0.0560   0.08449   0.07898  -0.0461   0.9092   0.0511
  -5.250  -0.0231   0.08230   0.07671  -0.0530   0.8889   0.0534
  -5.000   0.0181   0.08198   0.07620  -0.0630   0.8707   0.0546
  -4.750   0.0387   0.07793   0.07213  -0.0652   0.8547   0.0555
  -4.500   0.0488   0.07336   0.06753  -0.0636   0.8411   0.0581
  -4.250   0.0703   0.07074   0.06483  -0.0660   0.8268   0.0616
  -4.000   0.0971   0.06862   0.06261  -0.0699   0.8135   0.0651
  -3.750   0.1383   0.06789   0.06170  -0.0777   0.8004   0.0677
  -3.500   0.1733   0.06601   0.05970  -0.0833   0.7884   0.0685
  -3.250   0.1834   0.06171   0.05540  -0.0818   0.7788   0.0702
  -3.000   0.2068   0.05899   0.05256  -0.0835   0.7693   0.0734
  -2.750   0.2392   0.05699   0.05044  -0.0876   0.7589   0.0781
  -2.500   0.2946   0.05666   0.04983  -0.0970   0.7487   0.0814
  -2.250   0.3039   0.05250   0.04569  -0.0948   0.7409   0.0853
  -2.000   0.3583   0.05245   0.04536  -0.1032   0.7309   0.0944
  -1.750   0.3731   0.04865   0.04157  -0.1023   0.7233   0.0973
  -1.500   0.4052   0.04671   0.03950  -0.1051   0.7150   0.1030
  -1.000   0.4765   0.04316   0.03561  -0.1116   0.6997   0.1119
  -0.750   0.5132   0.04186   0.03413  -0.1147   0.6917   0.1186
  -0.500   0.5576   0.04108   0.03304  -0.1187   0.6848   0.1211
  -0.250   0.5921   0.03810   0.02987  -0.1210   0.6775   0.0782
   0.000   0.6275   0.03669   0.02821  -0.1231   0.6710   0.0778
   0.250   0.6622   0.03547   0.02679  -0.1251   0.6636   0.0775
   0.500   0.6977   0.03408   0.02514  -0.1268   0.6574   0.0730
   0.750   0.7344   0.03283   0.02359  -0.1287   0.6508   0.0703
   1.000   0.7675   0.03174   0.02223  -0.1297   0.6443   0.0707
   1.250   0.7992   0.03084   0.02106  -0.1305   0.6384   0.0731
   1.500   0.8296   0.03031   0.02030  -0.1311   0.6315   0.0849
   1.750   0.8637   0.02948   0.01899  -0.1317   0.6266   0.0962
   2.000   0.8924   0.02943   0.01877  -0.1323   0.6188   0.1174
   2.250   0.9230   0.02908   0.01804  -0.1323   0.6135   0.1365
   2.500   0.9521   0.02901   0.01765  -0.1326   0.6065   0.1468
   2.750   0.9798   0.02893   0.01740  -0.1324   0.6007   0.1582
   3.000   1.0060   0.02911   0.01745  -0.1322   0.5945   0.1749
   3.250   1.0318   0.02924   0.01750  -0.1318   0.5881   0.1855
   3.500   1.0578   0.02927   0.01743  -0.1311   0.5832   0.2026
   3.750   1.0810   0.02981   0.01807  -0.1309   0.5757   0.2235
   4.000   1.1064   0.02989   0.01817  -0.1302   0.5707   0.2451
   4.250   1.1289   0.03052   0.01891  -0.1299   0.5633   0.2740
   4.500   1.1536   0.03074   0.01920  -0.1293   0.5577   0.3108
   4.750   1.1764   0.03122   0.01992  -0.1289   0.5509   0.3669
   5.000   1.2013   0.03137   0.02046  -0.1285   0.5445   1.0000
   5.250   1.2247   0.03208   0.02119  -0.1279   0.5380   1.0000
   5.500   1.2470   0.03287   0.02198  -0.1272   0.5307   1.0000
   5.750   1.2700   0.03353   0.02266  -0.1264   0.5241   1.0000
   6.000   1.2915   0.03432   0.02354  -0.1257   0.5163   1.0000
   6.250   1.3129   0.03509   0.02440  -0.1248   0.5087   1.0000
   6.500   1.3354   0.03563   0.02512  -0.1238   0.5011   1.0000
   6.750   1.3543   0.03662   0.02629  -0.1230   0.4918   1.0000
   7.000   1.3804   0.03658   0.02631  -0.1218   0.4851   1.0000
   7.250   1.3969   0.03773   0.02769  -0.1208   0.4743   1.0000
   7.500   1.4161   0.03844   0.02859  -0.1196   0.4644   1.0000
   7.750   1.4433   0.03806   0.02832  -0.1182   0.4564   1.0000
   8.000   1.4592   0.03898   0.02960  -0.1169   0.4444   1.0000
   8.250   1.4762   0.03967   0.03053  -0.1155   0.4324   1.0000
   8.500   1.4941   0.04010   0.03119  -0.1139   0.4199   1.0000
   8.750   1.5120   0.04040   0.03173  -0.1122   0.4065   1.0000
   9.000   1.5289   0.04069   0.03226  -0.1104   0.3920   1.0000
   9.250   1.5448   0.04093   0.03273  -0.1085   0.3762   1.0000
   9.500   1.5609   0.04103   0.03303  -0.1065   0.3591   1.0000
   9.750   1.5670   0.04222   0.03455  -0.1043   0.3402   1.0000
  10.000   1.5727   0.04330   0.03582  -0.1020   0.3203   1.0000
  10.250   1.5756   0.04454   0.03716  -0.0996   0.3000   1.0000
  10.500   1.5713   0.04653   0.03925  -0.0971   0.2804   1.0000
  10.750   1.5696   0.04845   0.04116  -0.0951   0.2607   1.0000
  11.000   1.5622   0.05146   0.04422  -0.0938   0.2416   1.0000
  11.250   1.5559   0.05452   0.04726  -0.0927   0.2233   1.0000
  11.500   1.5496   0.05780   0.05048  -0.0918   0.2066   1.0000
  11.750   1.5416   0.06158   0.05425  -0.0913   0.1910   1.0000
  12.000   1.5334   0.06555   0.05823  -0.0910   0.1765   1.0000
  12.250   1.5257   0.06958   0.06227  -0.0908   0.1633   1.0000
  12.500   1.5179   0.07372   0.06640  -0.0908   0.1508   1.0000
  12.750   1.5095   0.07804   0.07076  -0.0910   0.1389   1.0000
  13.000   1.5006   0.08268   0.07549  -0.0914   0.1274   1.0000
  13.250   1.4920   0.08737   0.08027  -0.0920   0.1167   1.0000
  13.500   1.4814   0.09243   0.08539  -0.0930   0.1061   1.0000
  13.750   1.4702   0.09777   0.09075  -0.0944   0.0958   1.0000
  14.000   1.4588   0.10329   0.09622  -0.0962   0.0859   1.0000
  14.250   1.4468   0.10933   0.10235  -0.0986   0.0760   1.0000
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