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EPPLER 377 (MODIFIED) AIRFOIL (e377m-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 377 (MODIFIED) AIRFOIL (e377m-il)
Reynolds number: 100,000
Max Cl/Cd: 63.83 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e377m-il-100000-n5.txt
Download as CSV file: xf-e377m-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2157   0.10947   0.10504  -0.0161   1.0000   0.0192
  -8.000  -0.2088   0.10804   0.10369  -0.0171   1.0000   0.0193
  -7.750  -0.2022   0.10670   0.10245  -0.0182   1.0000   0.0194
  -7.500  -0.1935   0.10519   0.10103  -0.0198   1.0000   0.0195
  -7.250  -0.1702   0.10275   0.09862  -0.0255   0.9697   0.0195
  -7.000  -0.1384   0.09998   0.09580  -0.0333   0.9356   0.0196
  -6.750  -0.1177   0.09407   0.08988  -0.0362   0.9112   0.0199
  -6.500  -0.1041   0.08844   0.08420  -0.0365   0.8878   0.0210
  -6.250  -0.0859   0.08548   0.08116  -0.0389   0.8610   0.0221
  -6.000  -0.0687   0.08295   0.07854  -0.0411   0.8384   0.0233
  -5.750  -0.0515   0.08054   0.07602  -0.0433   0.8169   0.0246
  -5.500  -0.0333   0.07820   0.07360  -0.0457   0.7990   0.0256
  -5.250  -0.0126   0.07596   0.07126  -0.0486   0.7827   0.0270
  -5.000   0.0146   0.07451   0.06970  -0.0530   0.7679   0.0281
  -4.750   0.0475   0.07361   0.06868  -0.0589   0.7538   0.0286
  -4.500   0.0797   0.07226   0.06720  -0.0642   0.7410   0.0288
  -4.250   0.1039   0.06918   0.06406  -0.0672   0.7298   0.0290
  -4.000   0.1102   0.06388   0.05874  -0.0654   0.7209   0.0298
  -3.750   0.1298   0.06085   0.05564  -0.0669   0.7112   0.0309
  -3.500   0.1546   0.05840   0.05310  -0.0694   0.7017   0.0334
  -3.250   0.1879   0.05656   0.05112  -0.0735   0.6929   0.0381
  -3.000   0.2388   0.05645   0.05079  -0.0810   0.6835   0.0395
  -2.750   0.2807   0.05528   0.04944  -0.0864   0.6751   0.0398
  -2.500   0.2894   0.04982   0.04400  -0.0854   0.6684   0.0408
  -2.250   0.3133   0.04705   0.04117  -0.0869   0.6609   0.0424
  -2.000   0.3438   0.04496   0.03895  -0.0894   0.6539   0.0447
  -1.750   0.3776   0.04311   0.03695  -0.0924   0.6467   0.0479
  -1.500   0.4322   0.04356   0.03708  -0.0983   0.6396   0.0518
  -1.250   0.4499   0.03967   0.03320  -0.0987   0.6334   0.0533
  -1.000   0.4796   0.03776   0.03117  -0.1004   0.6269   0.0555
  -0.750   0.5124   0.03620   0.02945  -0.1024   0.6211   0.0579
  -0.500   0.5468   0.03484   0.02794  -0.1046   0.6144   0.0603
  -0.250   0.5844   0.03403   0.02687  -0.1067   0.6091   0.0624
   0.250   0.6567   0.02988   0.02225  -0.1108   0.5974   0.0393
   0.500   0.6817   0.02892   0.02126  -0.1112   0.5920   0.0458
   0.750   0.7144   0.02784   0.02002  -0.1123   0.5860   0.0474
   1.000   0.7468   0.02666   0.01860  -0.1131   0.5812   0.0460
   1.250   0.7790   0.02559   0.01735  -0.1139   0.5755   0.0457
   1.500   0.8106   0.02459   0.01615  -0.1145   0.5701   0.0465
   1.750   0.8425   0.02357   0.01483  -0.1148   0.5659   0.0490
   2.000   0.8706   0.02329   0.01451  -0.1149   0.5598   0.0591
   2.250   0.9000   0.02271   0.01375  -0.1149   0.5547   0.0679
   2.500   0.9285   0.02255   0.01339  -0.1147   0.5502   0.0841
   2.750   0.9557   0.02236   0.01315  -0.1146   0.5443   0.0949
   3.000   0.9827   0.02214   0.01281  -0.1144   0.5395   0.1037
   3.250   1.0109   0.02197   0.01246  -0.1142   0.5347   0.1085
   3.500   1.0369   0.02188   0.01241  -0.1141   0.5290   0.1173
   3.750   1.0638   0.02180   0.01223  -0.1138   0.5244   0.1236
   4.000   1.0902   0.02173   0.01214  -0.1136   0.5191   0.1263
   4.250   1.1165   0.02175   0.01214  -0.1133   0.5135   0.1304
   4.500   1.1428   0.02175   0.01209  -0.1130   0.5090   0.1392
   4.750   1.1694   0.02187   0.01230  -0.1128   0.5029   0.1417
   5.000   1.1962   0.02195   0.01235  -0.1126   0.4973   0.1433
   5.250   1.2227   0.02201   0.01240  -0.1123   0.4920   0.1454
   5.500   1.2481   0.02212   0.01262  -0.1120   0.4850   0.1516
   5.750   1.2741   0.02220   0.01263  -0.1114   0.4796   0.1555
   6.000   1.2985   0.02235   0.01300  -0.1110   0.4714   0.1564
   6.250   1.3236   0.02232   0.01298  -0.1103   0.4651   0.1578
   6.500   1.3472   0.02249   0.01332  -0.1097   0.4563   0.1595
   6.750   1.3715   0.02257   0.01347  -0.1090   0.4489   0.1617
   7.000   1.3953   0.02276   0.01377  -0.1083   0.4400   0.1674
   7.250   1.4185   0.02291   0.01408  -0.1076   0.4306   0.1719
   7.500   1.4420   0.02302   0.01435  -0.1069   0.4213   0.1740
   7.750   1.4649   0.02320   0.01467  -0.1061   0.4101   0.1760
   8.000   1.4873   0.02345   0.01507  -0.1052   0.3976   0.1781
   8.250   1.5092   0.02371   0.01548  -0.1044   0.3839   0.1804
   8.500   1.5306   0.02398   0.01589  -0.1034   0.3686   0.1840
   8.750   1.5510   0.02435   0.01638  -0.1024   0.3510   0.1909
   9.000   1.5703   0.02484   0.01710  -0.1013   0.3299   0.1967
   9.250   1.5879   0.02546   0.01780  -0.1000   0.3053   0.2007
   9.500   1.6032   0.02630   0.01866  -0.0985   0.2771   0.2039
   9.750   1.6139   0.02751   0.01978  -0.0967   0.2430   0.2072
  10.000   1.6187   0.02922   0.02131  -0.0945   0.2063   0.2106
  10.250   1.6189   0.03124   0.02317  -0.0920   0.1749   0.2137
  10.500   1.6159   0.03332   0.02517  -0.0892   0.1509   0.2172
  10.750   1.6090   0.03560   0.02741  -0.0864   0.1330   0.2212
  11.000   1.6014   0.03829   0.03008  -0.0844   0.1172   0.2260
  11.250   1.5938   0.04133   0.03312  -0.0831   0.1015   0.2310
  11.500   1.5859   0.04474   0.03655  -0.0823   0.0877   0.2371
  12.000   1.5673   0.05259   0.04437  -0.0819   0.0596   0.2488
  12.250   1.5561   0.05704   0.04883  -0.0820   0.0456   0.2549
  12.750   1.5360   0.06541   0.05780  -0.0826   0.0275   0.9605
  13.000   1.5242   0.07014   0.06259  -0.0830   0.0224   1.0000
  13.250   1.5147   0.07490   0.06745  -0.0836   0.0190   1.0000
  13.500   1.5035   0.08005   0.07270  -0.0845   0.0167   1.0000
  13.750   1.4924   0.08541   0.07817  -0.0857   0.0154   1.0000
  14.000   1.4838   0.09058   0.08353  -0.0869   0.0143   1.0000
  14.250   1.4751   0.09591   0.08905  -0.0883   0.0135   1.0000
  14.500   1.4663   0.10142   0.09474  -0.0899   0.0128   1.0000
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