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EPPLER 376 AIRFOIL (e376-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 376 AIRFOIL (e376-il)
Reynolds number: 1,000,000
Max Cl/Cd: 156.22 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e376-il-1000000.txt
Download as CSV file: xf-e376-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 376 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
  ------ -------- --------- --------- -------- -------- --------
   0.250   0.6690   0.02305   0.01877  -0.1105   0.5069   0.0098
   0.500   0.7014   0.02170   0.01732  -0.1116   0.5026   0.0098
   0.750   0.7334   0.02040   0.01591  -0.1126   0.4984   0.0098
   3.250   1.0366   0.00901   0.00310  -0.1153   0.4567   0.0157
   3.500   1.0640   0.00865   0.00269  -0.1151   0.4515   0.0146
   3.750   1.0909   0.00835   0.00227  -0.1148   0.4457   0.0147
   4.000   1.1180   0.00820   0.00204  -0.1146   0.4407   0.0196
   4.250   1.1451   0.00820   0.00208  -0.1144   0.4353   0.0487
   4.500   1.1717   0.00832   0.00219  -0.1143   0.4292   0.0597
   4.750   1.1987   0.00836   0.00227  -0.1141   0.4230   0.0699
   5.000   1.2254   0.00845   0.00238  -0.1140   0.4165   0.0816
   5.250   1.2522   0.00852   0.00248  -0.1139   0.4104   0.0990
   5.500   1.2788   0.00862   0.00261  -0.1137   0.4035   0.1175
   5.750   1.3054   0.00872   0.00273  -0.1136   0.3966   0.1339
   6.000   1.3317   0.00886   0.00289  -0.1134   0.3884   0.1522
   6.250   1.3582   0.00897   0.00307  -0.1133   0.3799   0.1708
   6.500   1.3843   0.00913   0.00325  -0.1131   0.3709   0.1928
   7.250   1.4591   0.00934   0.00413  -0.1126   0.2910   1.0000
   7.500   1.4807   0.01027   0.00471  -0.1121   0.2332   1.0000
   7.750   1.5018   0.01125   0.00542  -0.1116   0.1824   1.0000
   8.000   1.5223   0.01227   0.00617  -0.1110   0.1355   1.0000
   8.250   1.5408   0.01356   0.00710  -0.1102   0.0827   1.0000
   8.500   1.5559   0.01525   0.00838  -0.1090   0.0267   1.0000
   8.750   1.5728   0.01657   0.00955  -0.1078   0.0051   1.0000
   9.000   1.5943   0.01717   0.01024  -0.1070   0.0044   1.0000
   9.250   1.6150   0.01781   0.01097  -0.1062   0.0041   1.0000
   9.500   1.6346   0.01856   0.01181  -0.1053   0.0038   1.0000
   9.750   1.6523   0.01946   0.01281  -0.1042   0.0034   1.0000
  10.000   1.6675   0.02056   0.01403  -0.1027   0.0031   1.0000
  10.250   1.6795   0.02186   0.01547  -0.1009   0.0029   1.0000
  10.500   1.6868   0.02341   0.01718  -0.0985   0.0028   1.0000
  10.750   1.6889   0.02498   0.01889  -0.0954   0.0027   1.0000
  11.000   1.6827   0.02674   0.02078  -0.0916   0.0027   1.0000
  11.250   1.6797   0.02871   0.02287  -0.0891   0.0027   1.0000
  11.500   1.6749   0.03124   0.02553  -0.0872   0.0027   1.0000
  11.750   1.6701   0.03416   0.02858  -0.0860   0.0027   1.0000
  12.000   1.6657   0.03729   0.03184  -0.0852   0.0027   1.0000
  12.250   1.6639   0.04031   0.03497  -0.0847   0.0028   1.0000
  12.500   1.6585   0.04388   0.03867  -0.0843   0.0028   1.0000
  12.750   1.6553   0.04729   0.04220  -0.0840   0.0029   1.0000
  13.000   1.6507   0.05093   0.04597  -0.0838   0.0029   1.0000
  13.250   1.6444   0.05487   0.05006  -0.0836   0.0030   1.0000
  13.500   1.6377   0.05890   0.05425  -0.0834   0.0031   1.0000
  13.750   1.6307   0.06308   0.05857  -0.0833   0.0032   1.0000
  14.000   1.6251   0.06715   0.06278  -0.0834   0.0032   1.0000
  14.250   1.6202   0.07134   0.06709  -0.0838   0.0032   1.0000
  14.500   1.6145   0.07576   0.07165  -0.0843   0.0032   1.0000
  14.750   1.6064   0.08072   0.07682  -0.0846   0.0033   1.0000
  15.000   1.5947   0.08655   0.08290  -0.0850   0.0036   1.0000
  15.250   1.5820   0.09275   0.08931  -0.0863   0.0038   1.0000
  15.500   1.5665   0.09974   0.09651  -0.0883   0.0041   1.0000
  16.500   1.3165   0.13096   0.12863  -0.0936   0.0052   1.0000
  16.750   1.2602   0.14524   0.14343  -0.1009   0.0070   1.0000
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