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EPPLER 377 (MODIFIED) AIRFOIL (e377m-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 377 (MODIFIED) AIRFOIL (e377m-il)
Reynolds number: 50,000
Max Cl/Cd: 36.83 at α=9.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e377m-il-50000-n5.txt
Download as CSV file: xf-e377m-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2175   0.11178   0.10554  -0.0162   1.0000   0.0373
  -8.000  -0.2105   0.11007   0.10393  -0.0171   1.0000   0.0381
  -7.750  -0.2043   0.10877   0.10275  -0.0181   1.0000   0.0387
  -7.500  -0.1965   0.10771   0.10181  -0.0197   1.0000   0.0391
  -7.250  -0.1885   0.10690   0.10112  -0.0215   1.0000   0.0393
  -7.000  -0.1820   0.10647   0.10083  -0.0231   1.0000   0.0395
  -6.750  -0.1800   0.10630   0.10083  -0.0238   1.0000   0.0396
  -6.500  -0.1562   0.10443   0.09904  -0.0299   0.9836   0.0399
  -6.250  -0.1420   0.09561   0.09023  -0.0295   0.9712   0.0409
  -6.000  -0.1143   0.09084   0.08544  -0.0344   0.9546   0.0426
  -5.750  -0.0831   0.08709   0.08165  -0.0404   0.9356   0.0446
  -5.500  -0.0518   0.08382   0.07828  -0.0463   0.9173   0.0470
  -5.250  -0.0151   0.08156   0.07593  -0.0537   0.8989   0.0504
  -5.000   0.0332   0.08207   0.07626  -0.0645   0.8796   0.0516
  -4.750   0.0436   0.07616   0.07038  -0.0636   0.8652   0.0526
  -4.500   0.0620   0.07260   0.06676  -0.0649   0.8501   0.0545
  -4.250   0.0856   0.07000   0.06408  -0.0676   0.8354   0.0569
  -4.000   0.1121   0.06775   0.06172  -0.0709   0.8216   0.0596
  -3.750   0.1455   0.06627   0.06010  -0.0757   0.8085   0.0622
  -3.500   0.1892   0.06599   0.05956  -0.0826   0.7959   0.0632
  -3.250   0.2030   0.06173   0.05532  -0.0826   0.7845   0.0642
  -3.000   0.2232   0.05873   0.05226  -0.0836   0.7738   0.0666
  -2.750   0.2548   0.05695   0.05033  -0.0870   0.7638   0.0723
  -2.500   0.2997   0.05644   0.04958  -0.0928   0.7537   0.0747
  -2.250   0.3173   0.05284   0.04597  -0.0933   0.7442   0.0767
  -2.000   0.3462   0.05067   0.04366  -0.0955   0.7358   0.0797
  -1.750   0.3816   0.04925   0.04205  -0.0988   0.7267   0.0837
  -1.500   0.4259   0.04908   0.04161  -0.1033   0.7178   0.0855
  -1.250   0.4544   0.04656   0.03897  -0.1051   0.7104   0.0863
  -1.000   0.4798   0.04412   0.03647  -0.1064   0.7020   0.0883
  -0.750   0.5111   0.04251   0.03469  -0.1082   0.6954   0.0928
  -0.250   0.5784   0.04008   0.03189  -0.1123   0.6807   0.1002
   0.000   0.6093   0.03886   0.03056  -0.1140   0.6724   0.1021
   0.250   0.6422   0.03769   0.02918  -0.1154   0.6666   0.1033
   0.500   0.6741   0.03679   0.02813  -0.1169   0.6586   0.1029
   0.750   0.7098   0.03539   0.02641  -0.1183   0.6528   0.0800
   1.000   0.7456   0.03485   0.02556  -0.1197   0.6455   0.0743
   1.250   0.7745   0.03432   0.02489  -0.1200   0.6395   0.0853
   1.500   0.8017   0.03346   0.02396  -0.1206   0.6327   0.0908
   1.750   0.8325   0.03281   0.02308  -0.1211   0.6265   0.0909
   2.000   0.8614   0.03245   0.02255  -0.1213   0.6208   0.1039
   2.250   0.8896   0.03228   0.02222  -0.1215   0.6139   0.1186
   2.500   0.9192   0.03195   0.02162  -0.1213   0.6090   0.1335
   2.750   0.9456   0.03190   0.02146  -0.1218   0.6015   0.1539
   3.000   0.9755   0.03167   0.02094  -0.1218   0.5961   0.1531
   3.250   1.0019   0.03177   0.02092  -0.1221   0.5895   0.1738
   3.500   1.0294   0.03188   0.02085  -0.1219   0.5835   0.1749
   3.750   1.0567   0.03200   0.02083  -0.1217   0.5779   0.1749
   4.000   1.0814   0.03237   0.02116  -0.1216   0.5708   0.1858
   4.250   1.1085   0.03247   0.02110  -0.1210   0.5661   0.1912
   4.500   1.1308   0.03316   0.02184  -0.1207   0.5582   0.1912
   4.750   1.1563   0.03332   0.02194  -0.1200   0.5530   0.1925
   5.000   1.1777   0.03391   0.02272  -0.1196   0.5456   0.2007
   5.250   1.2014   0.03423   0.02305  -0.1188   0.5396   0.2063
   5.500   1.2228   0.03486   0.02376  -0.1181   0.5326   0.2069
   5.750   1.2452   0.03529   0.02427  -0.1173   0.5258   0.2080
   6.000   1.2661   0.03591   0.02500  -0.1164   0.5185   0.2095
   6.250   1.2882   0.03637   0.02564  -0.1155   0.5112   0.2149
   6.500   1.3075   0.03711   0.02655  -0.1147   0.5029   0.2218
   6.750   1.3312   0.03728   0.02682  -0.1136   0.4958   0.2262
   7.000   1.3482   0.03829   0.02801  -0.1126   0.4861   0.2278
   7.250   1.3761   0.03791   0.02770  -0.1114   0.4797   0.2304
   7.500   1.3909   0.03903   0.02907  -0.1103   0.4686   0.2328
   7.750   1.4082   0.03979   0.03014  -0.1091   0.4583   0.2371
   8.000   1.4327   0.03962   0.03014  -0.1079   0.4494   0.2470
   8.250   1.4530   0.03987   0.03060  -0.1065   0.4385   0.2559
   8.500   1.4688   0.04054   0.03153  -0.1050   0.4261   0.2614
   8.750   1.4855   0.04099   0.03223  -0.1034   0.4133   0.2671
   9.000   1.5024   0.04131   0.03280  -0.1017   0.3998   0.2743
   9.250   1.5185   0.04156   0.03331  -0.0999   0.3851   0.2850
   9.500   1.5328   0.04162   0.03395  -0.0979   0.3696   0.6119
  10.000   1.5493   0.04315   0.03595  -0.0935   0.3344   1.0000
  10.250   1.5506   0.04453   0.03747  -0.0910   0.3159   1.0000
  10.500   1.5536   0.04559   0.03857  -0.0884   0.2967   1.0000
  10.750   1.5479   0.04794   0.04101  -0.0864   0.2784   1.0000
  11.000   1.5437   0.05036   0.04347  -0.0848   0.2591   1.0000
  11.250   1.5410   0.05275   0.04579  -0.0834   0.2399   1.0000
  11.500   1.5342   0.05606   0.04912  -0.0826   0.2224   1.0000
  11.750   1.5277   0.05946   0.05251  -0.0819   0.2058   1.0000
  12.000   1.5207   0.06310   0.05612  -0.0814   0.1903   1.0000
  12.250   1.5139   0.06687   0.05988  -0.0810   0.1763   1.0000
  12.500   1.5067   0.07083   0.06385  -0.0809   0.1633   1.0000
  12.750   1.4992   0.07497   0.06801  -0.0809   0.1508   1.0000
  13.000   1.4917   0.07918   0.07224  -0.0811   0.1393   1.0000
  13.250   1.4850   0.08334   0.07641  -0.0813   0.1287   1.0000
  13.500   1.4768   0.08778   0.08095  -0.0818   0.1181   1.0000
  13.750   1.4670   0.09286   0.08617  -0.0829   0.1077   1.0000
  14.000   1.4575   0.09800   0.09139  -0.0841   0.0977   1.0000
  14.250   1.4464   0.10349   0.09690  -0.0859   0.0880   1.0000
  14.500   1.4345   0.10926   0.10260  -0.0883   0.0786   1.0000
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