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EPPLER 428 AIRFOIL (e428-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 428 AIRFOIL (e428-il)
Reynolds number: 50,000
Max Cl/Cd: 25.96 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e428-il-50000-n5.txt
Download as CSV file: xf-e428-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 428 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.7823   0.07500   0.06763  -0.0175   1.0000   0.0984
 -10.750  -0.8038   0.06771   0.06033  -0.0226   1.0000   0.1010
 -10.500  -0.8827   0.05301   0.04527  -0.0307   1.0000   0.0924
 -10.250  -0.9026   0.04779   0.03957  -0.0316   1.0000   0.0965
 -10.000  -0.8882   0.04804   0.03995  -0.0307   1.0000   0.1066
  -9.750  -0.8708   0.04868   0.04066  -0.0297   1.0000   0.1176
  -9.500  -0.8602   0.04747   0.03935  -0.0291   1.0000   0.1261
  -9.250  -0.8542   0.04485   0.03639  -0.0288   1.0000   0.1332
  -9.000  -0.8396   0.04309   0.03448  -0.0281   1.0000   0.1388
  -8.750  -0.8247   0.04128   0.03244  -0.0275   1.0000   0.1453
  -8.500  -0.8103   0.03911   0.02997  -0.0270   1.0000   0.1515
  -8.250  -0.7906   0.03786   0.02860  -0.0263   1.0000   0.1575
  -8.000  -0.7742   0.03580   0.02618  -0.0258   1.0000   0.1649
  -7.750  -0.7524   0.03495   0.02530  -0.0250   1.0000   0.1717
  -7.500  -0.7333   0.03324   0.02324  -0.0245   1.0000   0.1797
  -7.250  -0.7109   0.03242   0.02239  -0.0238   1.0000   0.1869
  -7.000  -0.6899   0.03116   0.02087  -0.0232   1.0000   0.1959
  -6.750  -0.6672   0.03034   0.01997  -0.0225   1.0000   0.2044
  -6.500  -0.6449   0.02939   0.01887  -0.0218   1.0000   0.2136
  -6.250  -0.6224   0.02852   0.01780  -0.0212   1.0000   0.2244
  -6.000  -0.5993   0.02789   0.01719  -0.0204   1.0000   0.2340
  -5.750  -0.5764   0.02708   0.01622  -0.0198   1.0000   0.2453
  -5.500  -0.5530   0.02634   0.01541  -0.0191   1.0000   0.2555
  -5.250  -0.5295   0.02560   0.01463  -0.0184   1.0000   0.2652
  -5.000  -0.5059   0.02482   0.01364  -0.0178   1.0000   0.2761
  -4.750  -0.4822   0.02416   0.01308  -0.0170   1.0000   0.2847
  -4.500  -0.4584   0.02349   0.01232  -0.0163   1.0000   0.2954
  -4.250  -0.4349   0.02290   0.01172  -0.0155   1.0000   0.3059
  -4.000  -0.4114   0.02232   0.01116  -0.0147   1.0000   0.3163
  -3.750  -0.3879   0.02179   0.01059  -0.0140   1.0000   0.3283
  -3.500  -0.3648   0.02130   0.01014  -0.0131   1.0000   0.3400
  -3.250  -0.3417   0.02084   0.00976  -0.0123   1.0000   0.3528
  -3.000  -0.3187   0.02041   0.00939  -0.0115   1.0000   0.3666
  -2.750  -0.2966   0.02002   0.00906  -0.0106   1.0000   0.3814
  -2.500  -0.2749   0.01967   0.00881  -0.0096   1.0000   0.3976
  -2.250  -0.2539   0.01936   0.00861  -0.0086   1.0000   0.4148
  -2.000  -0.2339   0.01908   0.00847  -0.0075   1.0000   0.4342
  -1.750  -0.2148   0.01886   0.00840  -0.0063   1.0000   0.4562
  -1.500  -0.1934   0.01868   0.00839  -0.0057   0.9976   0.4827
  -1.250  -0.1500   0.01850   0.00847  -0.0090   0.9776   0.5237
  -1.000  -0.1074   0.01832   0.00857  -0.0117   0.9579   0.5722
  -0.750  -0.0646   0.01815   0.00867  -0.0141   0.9380   0.6275
  -0.500  -0.0226   0.01794   0.00870  -0.0157   0.9118   0.6836
  -0.250   0.0183   0.01770   0.00865  -0.0166   0.8805   0.7389
   0.000   0.0562   0.01750   0.00856  -0.0166   0.8468   0.7908
   0.250   0.0937   0.01736   0.00847  -0.0166   0.8147   0.8418
   0.500   0.1358   0.01727   0.00836  -0.0177   0.7822   0.8915
   0.750   0.1836   0.01722   0.00821  -0.0203   0.7456   0.9378
   1.000   0.2327   0.01719   0.00802  -0.0235   0.7055   0.9829
   1.250   0.2611   0.01728   0.00791  -0.0235   0.6692   1.0000
   1.500   0.2806   0.01744   0.00787  -0.0217   0.6346   1.0000
   1.750   0.3009   0.01764   0.00786  -0.0200   0.5987   1.0000
   2.000   0.3219   0.01788   0.00787  -0.0184   0.5610   1.0000
   2.250   0.3435   0.01816   0.00794  -0.0169   0.5215   1.0000
   2.500   0.3654   0.01850   0.00805  -0.0156   0.4820   1.0000
   2.750   0.3877   0.01891   0.00820  -0.0144   0.4447   1.0000
   3.000   0.4106   0.01937   0.00844  -0.0133   0.4117   1.0000
   3.250   0.4346   0.01987   0.00876  -0.0126   0.3831   1.0000
   3.500   0.4590   0.02042   0.00911  -0.0119   0.3604   1.0000
   3.750   0.4840   0.02098   0.00953  -0.0114   0.3413   1.0000
   4.000   0.5091   0.02157   0.01001  -0.0109   0.3250   1.0000
   4.250   0.5342   0.02218   0.01052  -0.0104   0.3110   1.0000
   4.500   0.5598   0.02281   0.01114  -0.0099   0.2984   1.0000
   4.750   0.5852   0.02349   0.01181  -0.0094   0.2876   1.0000
   5.000   0.6104   0.02420   0.01240  -0.0089   0.2780   1.0000
   5.250   0.6358   0.02494   0.01325  -0.0085   0.2680   1.0000
   5.500   0.6612   0.02574   0.01396  -0.0080   0.2603   1.0000
   5.750   0.6861   0.02658   0.01496  -0.0076   0.2512   1.0000
   6.000   0.7113   0.02742   0.01571  -0.0071   0.2439   1.0000
   6.250   0.7354   0.02840   0.01693  -0.0066   0.2356   1.0000
   6.500   0.7602   0.02928   0.01777  -0.0061   0.2286   1.0000
   6.750   0.7831   0.03038   0.01911  -0.0056   0.2204   1.0000
   7.000   0.8070   0.03133   0.02009  -0.0050   0.2132   1.0000
   7.250   0.8289   0.03250   0.02148  -0.0044   0.2053   1.0000
   7.500   0.8515   0.03349   0.02254  -0.0038   0.1977   1.0000
   7.750   0.8724   0.03473   0.02398  -0.0032   0.1903   1.0000
   8.000   0.8932   0.03591   0.02534  -0.0025   0.1830   1.0000
   8.250   0.9145   0.03708   0.02657  -0.0018   0.1768   1.0000
   8.500   0.9313   0.03880   0.02865  -0.0011   0.1697   1.0000
   8.750   0.9535   0.03977   0.02961  -0.0004   0.1644   1.0000
   9.000   0.9662   0.04206   0.03231   0.0004   0.1583   1.0000
   9.250   0.9809   0.04400   0.03451   0.0012   0.1531   1.0000
   9.500   1.0029   0.04502   0.03548   0.0019   0.1489   1.0000
   9.750   1.0034   0.04852   0.03953   0.0028   0.1438   1.0000
  10.000   1.0087   0.05119   0.04248   0.0036   0.1393   1.0000
  10.250   1.0245   0.05270   0.04405   0.0044   0.1357   1.0000
  10.500   1.0224   0.05615   0.04777   0.0052   0.1329   1.0000
  10.750   0.9896   0.06226   0.05426   0.0052   0.1310   1.0000
  11.000   0.9344   0.07063   0.06281   0.0027   0.1306   1.0000
  11.250   0.8310   0.09254   0.08467  -0.0135   0.1301   1.0000
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