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EPPLER 377 AIRFOIL (e377-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 377 AIRFOIL (e377-il)
Reynolds number: 1,000,000
Max Cl/Cd: 167.27 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e377-il-1000000.txt
Download as CSV file: xf-e377-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.2817   0.14403   0.14257   0.0005   1.0000   0.0036
 -12.500  -0.2742   0.14109   0.13964  -0.0009   1.0000   0.0036
  -6.500  -0.1023   0.08451   0.08186  -0.0354   0.6642   0.0060
  -6.000  -0.0768   0.07849   0.07579  -0.0383   0.6449   0.0062
  -5.750  -0.0606   0.07612   0.07337  -0.0405   0.6365   0.0064
  -5.500  -0.0432   0.07372   0.07095  -0.0429   0.6276   0.0065
  -5.250  -0.0243   0.07127   0.06846  -0.0455   0.6198   0.0067
  -5.000  -0.0042   0.06879   0.06594  -0.0483   0.6125   0.0069
  -4.750   0.0175   0.06628   0.06340  -0.0514   0.6055   0.0072
  -4.500   0.0406   0.06369   0.06077  -0.0546   0.5989   0.0076
  -4.250   0.0656   0.06107   0.05811  -0.0581   0.5928   0.0082
  -4.000   0.0947   0.05845   0.05545  -0.0622   0.5867   0.0087
  -3.750   0.1267   0.05577   0.05271  -0.0671   0.5809   0.0088
  -3.500   0.1591   0.05296   0.04986  -0.0718   0.5752   0.0089
  -3.250   0.1932   0.05001   0.04683  -0.0766   0.5699   0.0089
  -3.000   0.2220   0.04621   0.04298  -0.0805   0.5651   0.0093
  -2.750   0.2502   0.04425   0.04098  -0.0832   0.5597   0.0099
  -2.500   0.2827   0.04214   0.03880  -0.0867   0.5546   0.0109
  -2.250   0.3204   0.03984   0.03643  -0.0909   0.5499   0.0124
  -2.000   0.3625   0.03766   0.03416  -0.0958   0.5450   0.0129
  -1.750   0.4003   0.03532   0.03173  -0.0997   0.5402   0.0130
  -1.500   0.4391   0.03279   0.02912  -0.1035   0.5359   0.0130
   0.750   0.7709   0.00998   0.00445  -0.1250   0.4982   0.0184
   1.250   0.8276   0.00882   0.00292  -0.1248   0.4900   0.0188
   1.500   0.8554   0.00841   0.00236  -0.1246   0.4856   0.0188
   1.750   0.8830   0.00818   0.00202  -0.1243   0.4812   0.0193
   2.000   0.9107   0.00794   0.00173  -0.1241   0.4772   0.0242
   2.250   0.9381   0.00787   0.00169  -0.1238   0.4727   0.0436
   2.500   0.9652   0.00795   0.00176  -0.1236   0.4679   0.0569
   2.750   0.9926   0.00800   0.00183  -0.1234   0.4637   0.0631
   3.000   1.0199   0.00799   0.00184  -0.1232   0.4587   0.0704
   3.250   1.0469   0.00808   0.00189  -0.1229   0.4534   0.0761
   3.500   1.0742   0.00808   0.00194  -0.1227   0.4482   0.0872
   3.750   1.1012   0.00813   0.00199  -0.1225   0.4423   0.0985
   4.000   1.1283   0.00819   0.00208  -0.1223   0.4368   0.1106
   4.250   1.1554   0.00824   0.00215  -0.1221   0.4309   0.1227
   4.500   1.1821   0.00835   0.00226  -0.1219   0.4250   0.1353
   4.750   1.2092   0.00839   0.00235  -0.1217   0.4193   0.1506
   5.000   1.2359   0.00850   0.00247  -0.1215   0.4127   0.1668
   5.250   1.2628   0.00857   0.00261  -0.1213   0.4063   0.1848
   5.500   1.2893   0.00869   0.00275  -0.1211   0.3989   0.2095
   5.750   1.3160   0.00877   0.00290  -0.1209   0.3919   0.2409
   6.000   1.3423   0.00891   0.00308  -0.1207   0.3835   0.2828
   6.250   1.3699   0.00819   0.00336  -0.1210   0.3745   1.0000
   6.500   1.3961   0.00837   0.00352  -0.1207   0.3654   1.0000
   6.750   1.4220   0.00859   0.00370  -0.1205   0.3540   1.0000
   7.000   1.4477   0.00883   0.00390  -0.1202   0.3401   1.0000
   7.250   1.4725   0.00920   0.00417  -0.1198   0.3147   1.0000
   7.500   1.4962   0.00975   0.00457  -0.1194   0.2790   1.0000
   7.750   1.5175   0.01068   0.00518  -0.1188   0.2250   1.0000
   8.000   1.5372   0.01184   0.00598  -0.1180   0.1677   1.0000
   8.250   1.5580   0.01276   0.00668  -0.1174   0.1305   1.0000
   8.750   1.5975   0.01473   0.00822  -0.1157   0.0650   1.0000
   9.000   1.6123   0.01628   0.00948  -0.1144   0.0243   1.0000
   9.250   1.6267   0.01777   0.01083  -0.1129   0.0045   1.0000
   9.500   1.6467   0.01847   0.01162  -0.1119   0.0039   1.0000
   9.750   1.6654   0.01926   0.01249  -0.1108   0.0035   1.0000
  10.000   1.6827   0.02013   0.01344  -0.1095   0.0032   1.0000
  10.250   1.6970   0.02123   0.01465  -0.1079   0.0029   1.0000
  10.500   1.7083   0.02247   0.01605  -0.1060   0.0027   1.0000
  10.750   1.7151   0.02392   0.01763  -0.1035   0.0027   1.0000
  11.000   1.7187   0.02512   0.01893  -0.1004   0.0026   1.0000
  11.250   1.7197   0.02645   0.02036  -0.0974   0.0026   1.0000
  11.500   1.7200   0.02811   0.02212  -0.0951   0.0026   1.0000
  11.750   1.7188   0.03022   0.02435  -0.0933   0.0025   1.0000
  12.000   1.7200   0.03239   0.02662  -0.0921   0.0024   1.0000
  12.250   1.7166   0.03529   0.02964  -0.0911   0.0024   1.0000
  12.500   1.7137   0.03834   0.03281  -0.0905   0.0024   1.0000
  12.750   1.7108   0.04153   0.03612  -0.0901   0.0023   1.0000
  13.000   1.7058   0.04510   0.03981  -0.0899   0.0023   1.0000
  13.250   1.7007   0.04879   0.04362  -0.0899   0.0022   1.0000
  13.500   1.6937   0.05280   0.04775  -0.0899   0.0022   1.0000
  13.750   1.6863   0.05699   0.05207  -0.0902   0.0021   1.0000
  14.000   1.6790   0.06123   0.05642  -0.0906   0.0021   1.0000
  14.250   1.6717   0.06559   0.06089  -0.0911   0.0020   1.0000
  14.500   1.6628   0.07035   0.06577  -0.0919   0.0019   1.0000
  14.750   1.6551   0.07513   0.07067  -0.0928   0.0019   1.0000
  15.000   1.6471   0.08009   0.07575  -0.0940   0.0019   1.0000
  15.250   1.6390   0.08520   0.08096  -0.0952   0.0018   1.0000
  15.500   1.6308   0.09048   0.08636  -0.0967   0.0018   1.0000
  15.750   1.6225   0.09589   0.09189  -0.0982   0.0017   1.0000
  16.000   1.6139   0.10143   0.09756  -0.1000   0.0017   1.0000
  16.250   1.6056   0.10709   0.10334  -0.1018   0.0017   1.0000
  16.500   1.5972   0.11285   0.10923  -0.1039   0.0017   1.0000
  16.750   1.5886   0.11873   0.11524  -0.1061   0.0017   1.0000
  17.000   1.5798   0.12476   0.12140  -0.1085   0.0017   1.0000
  17.250   1.5709   0.13096   0.12775  -0.1111   0.0017   1.0000
  17.500   1.5619   0.13730   0.13423  -0.1140   0.0018   1.0000
  17.750   1.5517   0.14398   0.14109  -0.1172   0.0018   1.0000
  18.000   1.5398   0.15133   0.14862  -0.1210   0.0019   1.0000
  18.250   1.5282   0.15885   0.15631  -0.1252   0.0019   1.0000
  18.500   1.5162   0.16671   0.16434  -0.1298   0.0020   1.0000
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