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EPPLER 328 AIRFOIL (e328-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 328 AIRFOIL (e328-il)
Reynolds number: 1,000,000
Max Cl/Cd: 105.12 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e328-il-1000000-n5.txt
Download as CSV file: xf-e328-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 328 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2677   0.09212   0.08978  -0.0370   0.7521   0.0048
 -10.500  -0.2673   0.08820   0.08579  -0.0384   0.7330   0.0048
 -10.250  -0.3713   0.09285   0.09115  -0.0348   0.9415   0.0049
 -10.000  -0.3283   0.08426   0.08208  -0.0516   0.8310   0.0046
  -9.750  -0.3346   0.08053   0.07814  -0.0526   0.7773   0.0045
  -9.500  -0.3494   0.07436   0.07191  -0.0563   0.7528   0.0043
  -9.250  -0.3635   0.06931   0.06676  -0.0601   0.7268   0.0043
  -8.250  -0.5907   0.02264   0.01794  -0.0357   0.7032   0.0031
  -8.000  -0.5768   0.02041   0.01531  -0.0336   0.6863   0.0032
  -7.750  -0.5583   0.01898   0.01359  -0.0321   0.6703   0.0032
  -7.500  -0.5368   0.01806   0.01245  -0.0310   0.6557   0.0033
  -7.250  -0.5163   0.01687   0.01102  -0.0298   0.6412   0.0032
  -7.000  -0.4955   0.01555   0.00942  -0.0286   0.6279   0.0035
  -6.750  -0.4725   0.01486   0.00859  -0.0278   0.6150   0.0036
  -6.500  -0.4490   0.01428   0.00789  -0.0270   0.6031   0.0037
  -6.250  -0.4249   0.01384   0.00735  -0.0263   0.5919   0.0038
  -6.000  -0.3999   0.01360   0.00705  -0.0258   0.5805   0.0040
  -5.750  -0.3757   0.01316   0.00651  -0.0251   0.5693   0.0041
  -5.500  -0.3511   0.01283   0.00610  -0.0244   0.5581   0.0043
  -5.250  -0.3268   0.01246   0.00564  -0.0238   0.5479   0.0044
  -5.000  -0.3021   0.01213   0.00523  -0.0231   0.5389   0.0045
  -4.750  -0.2777   0.01182   0.00484  -0.0225   0.5297   0.0047
  -4.500  -0.2525   0.01157   0.00454  -0.0219   0.5200   0.0049
  -4.250  -0.2278   0.01132   0.00422  -0.0213   0.5107   0.0050
  -4.000  -0.2027   0.01109   0.00393  -0.0207   0.5020   0.0051
  -3.750  -0.1775   0.01086   0.00365  -0.0201   0.4947   0.0051
  -3.500  -0.1527   0.01060   0.00334  -0.0195   0.4865   0.0054
  -3.250  -0.1275   0.01040   0.00310  -0.0190   0.4790   0.0057
  -3.000  -0.1017   0.01027   0.00292  -0.0186   0.4707   0.0061
  -2.750  -0.0760   0.01011   0.00273  -0.0181   0.4638   0.0067
  -2.500  -0.0499   0.00999   0.00258  -0.0177   0.4569   0.0072
  -2.250  -0.0242   0.00984   0.00239  -0.0173   0.4503   0.0084
  -2.000   0.0019   0.00972   0.00224  -0.0169   0.4435   0.0102
  -1.750   0.0276   0.00959   0.00212  -0.0164   0.4366   0.0176
  -1.500   0.0538   0.00946   0.00202  -0.0161   0.4312   0.0289
  -1.250   0.0799   0.00936   0.00194  -0.0158   0.4252   0.0418
  -1.000   0.1050   0.00918   0.00186  -0.0153   0.4194   0.0816
  -0.750   0.1273   0.00872   0.00176  -0.0144   0.4143   0.1977
  -0.500   0.1243   0.00649   0.00149  -0.0091   0.4100   0.7663
  -0.250   0.1510   0.00655   0.00155  -0.0088   0.4047   0.7974
   0.000   0.1787   0.00661   0.00159  -0.0086   0.4000   0.8116
   0.250   0.2059   0.00671   0.00166  -0.0083   0.3944   0.8259
   0.500   0.2332   0.00682   0.00173  -0.0081   0.3892   0.8336
   0.750   0.2610   0.00690   0.00178  -0.0080   0.3851   0.8407
   1.000   0.2888   0.00696   0.00182  -0.0080   0.3804   0.8444
   1.250   0.3168   0.00703   0.00183  -0.0080   0.3752   0.8455
   1.500   0.3452   0.00708   0.00185  -0.0082   0.3711   0.8465
   1.750   0.3735   0.00714   0.00187  -0.0083   0.3669   0.8474
   2.000   0.4016   0.00721   0.00189  -0.0084   0.3621   0.8484
   2.250   0.4296   0.00728   0.00193  -0.0085   0.3577   0.8496
   2.500   0.4579   0.00734   0.00197  -0.0087   0.3541   0.8507
   2.750   0.4860   0.00741   0.00201  -0.0088   0.3496   0.8517
   3.000   0.5138   0.00749   0.00206  -0.0089   0.3453   0.8527
   3.250   0.5419   0.00757   0.00211  -0.0090   0.3416   0.8536
   3.500   0.5700   0.00764   0.00216  -0.0092   0.3376   0.8544
   3.750   0.5978   0.00773   0.00223  -0.0093   0.3331   0.8553
   4.000   0.6252   0.00783   0.00231  -0.0093   0.3285   0.8562
   4.250   0.6531   0.00789   0.00238  -0.0095   0.3249   0.8573
   4.500   0.6807   0.00797   0.00246  -0.0095   0.3204   0.8584
   4.750   0.7079   0.00808   0.00256  -0.0095   0.3158   0.8596
   5.000   0.7352   0.00817   0.00266  -0.0096   0.3117   0.8608
   5.250   0.7627   0.00826   0.00275  -0.0097   0.3072   0.8619
   5.500   0.7897   0.00839   0.00287  -0.0097   0.3015   0.8630
   5.750   0.8167   0.00851   0.00298  -0.0097   0.2965   0.8641
   6.000   0.8438   0.00862   0.00310  -0.0097   0.2908   0.8653
   6.250   0.8702   0.00878   0.00324  -0.0097   0.2848   0.8666
   6.500   0.8972   0.00890   0.00337  -0.0097   0.2793   0.8678
   6.750   0.9235   0.00906   0.00352  -0.0096   0.2724   0.8690
   7.000   0.9498   0.00921   0.00367  -0.0096   0.2660   0.8702
   7.250   0.9757   0.00940   0.00384  -0.0095   0.2577   0.8713
   7.500   1.0013   0.00957   0.00402  -0.0093   0.2500   0.8727
   7.750   1.0260   0.00980   0.00423  -0.0090   0.2408   0.8743
   8.000   1.0510   0.01000   0.00444  -0.0087   0.2321   0.8760
   8.250   1.0754   0.01023   0.00467  -0.0084   0.2232   0.8777
   8.500   1.0990   0.01053   0.00493  -0.0079   0.2119   0.8794
   8.750   1.1222   0.01083   0.00521  -0.0074   0.2007   0.8812
   9.000   1.1452   0.01114   0.00550  -0.0069   0.1892   0.8830
   9.250   1.1670   0.01152   0.00584  -0.0062   0.1760   0.8849
   9.500   1.1880   0.01193   0.00621  -0.0054   0.1628   0.8868
   9.750   1.2077   0.01237   0.00660  -0.0044   0.1492   0.8889
  10.000   1.2269   0.01280   0.00702  -0.0033   0.1371   0.8913
  10.250   1.2435   0.01335   0.00751  -0.0018   0.1222   0.8941
  10.500   1.2604   0.01385   0.00799  -0.0004   0.1107   0.8972
  10.750   1.2765   0.01436   0.00848   0.0012   0.1004   0.9004
  11.000   1.2909   0.01484   0.00895   0.0031   0.0924   0.9039
  11.250   1.2997   0.01538   0.00949   0.0059   0.0831   0.9090
  11.500   1.3062   0.01606   0.01015   0.0091   0.0727   0.9153
  11.750   1.3166   0.01659   0.01072   0.0115   0.0675   0.9214
  12.000   1.3203   0.01737   0.01151   0.0147   0.0584   0.9308
  12.250   1.3261   0.01809   0.01227   0.0175   0.0540   0.9430
  12.500   1.3363   0.01889   0.01314   0.0190   0.0490   0.9626
  13.000   1.3547   0.02153   0.01581   0.0202   0.0366   1.0000
  13.500   1.3606   0.02466   0.01899   0.0227   0.0293   1.0000
  13.750   1.3586   0.02685   0.02120   0.0236   0.0247   1.0000
  14.000   1.3630   0.02867   0.02308   0.0241   0.0237   1.0000
  14.250   1.3610   0.03117   0.02562   0.0244   0.0206   1.0000
  14.500   1.3665   0.03307   0.02762   0.0245   0.0211   1.0000
  14.750   1.3615   0.03606   0.03065   0.0244   0.0182   1.0000
  15.000   1.3581   0.03898   0.03363   0.0242   0.0166   1.0000
  15.250   1.3517   0.04228   0.03698   0.0239   0.0148   1.0000
  15.500   1.3492   0.04527   0.04006   0.0235   0.0142   1.0000
  15.750   1.3431   0.04866   0.04352   0.0229   0.0131   1.0000
  16.000   1.3373   0.05215   0.04709   0.0222   0.0125   1.0000
  16.250   1.3321   0.05568   0.05069   0.0214   0.0121   1.0000
  16.500   1.3267   0.05928   0.05438   0.0204   0.0115   1.0000
  16.750   1.3196   0.06324   0.05841   0.0193   0.0105   1.0000
  17.000   1.3133   0.06717   0.06241   0.0181   0.0101   1.0000
  17.250   1.3050   0.07141   0.06672   0.0167   0.0091   1.0000
  17.500   1.2992   0.07544   0.07083   0.0153   0.0086   1.0000
  17.750   1.2941   0.07946   0.07494   0.0138   0.0084   1.0000
  18.000   1.2883   0.08361   0.07915   0.0122   0.0080   1.0000
  18.250   1.2794   0.08829   0.08390   0.0104   0.0072   1.0000
  18.500   1.2746   0.09247   0.08817   0.0086   0.0073   1.0000
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