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EPPLER 344 AIRFOIL (e344-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 344 AIRFOIL (e344-il)
Reynolds number: 500,000
Max Cl/Cd: 91.41 at α=9.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e344-il-500000-n5.txt
Download as CSV file: xf-e344-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 344 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.1274   0.09068   0.08715  -0.0559   0.6307   0.0129
 -10.250  -0.1229   0.08759   0.08402  -0.0567   0.6212   0.0129
 -10.000  -0.1265   0.08262   0.07904  -0.0587   0.6149   0.0130
  -9.750  -0.1293   0.07792   0.07432  -0.0606   0.6087   0.0130
  -9.500  -0.1291   0.07403   0.07041  -0.0619   0.6009   0.0130
  -9.000  -0.1385   0.06437   0.06074  -0.0660   0.5895   0.0130
  -8.750  -0.1425   0.06005   0.05641  -0.0681   0.5831   0.0130
  -8.250  -0.1687   0.05016   0.04646  -0.0744   0.5741   0.0130
  -7.750  -0.2355   0.05714   0.05314  -0.0736   0.5770   0.0098
  -7.500  -0.2393   0.05373   0.04963  -0.0722   0.5700   0.0098
  -7.250  -0.2404   0.05035   0.04610  -0.0705   0.5631   0.0098
  -7.000  -0.2374   0.04744   0.04305  -0.0688   0.5560   0.0094
  -6.750  -0.2336   0.04413   0.03956  -0.0667   0.5488   0.0094
  -6.500  -0.2279   0.04078   0.03598  -0.0644   0.5419   0.0095
  -6.250  -0.2211   0.03688   0.03182  -0.0616   0.5359   0.0098
  -6.000  -0.2112   0.03397   0.02867  -0.0592   0.5292   0.0097
  -5.500  -0.2044   0.02090   0.01413  -0.0496   0.5210   0.0081
  -5.250  -0.1830   0.01928   0.01215  -0.0482   0.5139   0.0080
  -5.000  -0.1600   0.01809   0.01070  -0.0472   0.5075   0.0080
  -4.750  -0.1359   0.01706   0.00947  -0.0463   0.5006   0.0080
  -4.250  -0.0866   0.01555   0.00765  -0.0449   0.4871   0.0081
  -4.000  -0.0619   0.01497   0.00696  -0.0442   0.4803   0.0083
  -3.750  -0.0373   0.01447   0.00637  -0.0435   0.4744   0.0083
  -3.500  -0.0126   0.01402   0.00586  -0.0428   0.4685   0.0085
  -3.250   0.0118   0.01365   0.00542  -0.0421   0.4628   0.0086
  -3.000   0.0362   0.01330   0.00501  -0.0413   0.4579   0.0090
  -2.750   0.0607   0.01299   0.00465  -0.0406   0.4528   0.0093
  -2.500   0.0851   0.01273   0.00433  -0.0398   0.4475   0.0095
  -2.250   0.1097   0.01251   0.00404  -0.0391   0.4428   0.0102
  -2.000   0.1345   0.01227   0.00378  -0.0384   0.4378   0.0107
  -1.750   0.1594   0.01210   0.00357  -0.0378   0.4330   0.0117
  -1.500   0.1844   0.01198   0.00339  -0.0372   0.4287   0.0128
  -1.250   0.2098   0.01183   0.00323  -0.0366   0.4250   0.0152
  -1.000   0.2352   0.01170   0.00311  -0.0361   0.4211   0.0197
  -0.750   0.2602   0.01156   0.00300  -0.0355   0.4171   0.0314
  -0.500   0.2849   0.01144   0.00293  -0.0349   0.4133   0.0543
  -0.250   0.3094   0.01125   0.00288  -0.0343   0.4097   0.0997
   0.000   0.3176   0.00980   0.00272  -0.0312   0.4068   0.5038
   0.250   0.3178   0.00905   0.00324  -0.0247   0.4040   0.8678
   0.500   0.3399   0.00931   0.00344  -0.0230   0.4008   0.8908
   0.750   0.3632   0.00959   0.00367  -0.0216   0.3977   0.9009
   1.000   0.3861   0.00980   0.00382  -0.0202   0.3950   0.9100
   1.250   0.4077   0.01004   0.00404  -0.0183   0.3923   0.9213
   1.500   0.4330   0.01022   0.00420  -0.0173   0.3892   0.9273
   1.750   0.4592   0.01028   0.00419  -0.0170   0.3859   0.9289
   2.000   0.4850   0.01033   0.00418  -0.0167   0.3829   0.9302
   2.250   0.5105   0.01040   0.00418  -0.0163   0.3803   0.9314
   2.500   0.5367   0.01043   0.00418  -0.0161   0.3781   0.9326
   2.750   0.5627   0.01047   0.00419  -0.0158   0.3753   0.9339
   3.000   0.5888   0.01051   0.00421  -0.0156   0.3725   0.9350
   3.250   0.6148   0.01057   0.00423  -0.0154   0.3697   0.9359
   3.500   0.6408   0.01065   0.00427  -0.0152   0.3673   0.9368
   3.750   0.6666   0.01074   0.00431  -0.0150   0.3649   0.9376
   4.000   0.6931   0.01080   0.00437  -0.0149   0.3626   0.9384
   4.250   0.7195   0.01086   0.00444  -0.0147   0.3601   0.9393
   4.500   0.7458   0.01093   0.00451  -0.0146   0.3575   0.9400
   4.750   0.7719   0.01102   0.00459  -0.0145   0.3550   0.9408
   5.000   0.7975   0.01112   0.00467  -0.0142   0.3523   0.9416
   5.250   0.8227   0.01124   0.00477  -0.0140   0.3499   0.9425
   5.500   0.8485   0.01134   0.00488  -0.0138   0.3478   0.9434
   5.750   0.8746   0.01142   0.00498  -0.0137   0.3454   0.9443
   6.000   0.9003   0.01152   0.00510  -0.0135   0.3426   0.9453
   6.250   0.9256   0.01162   0.00522  -0.0133   0.3400   0.9464
   6.500   0.9502   0.01175   0.00535  -0.0130   0.3373   0.9477
   6.750   0.9745   0.01190   0.00549  -0.0126   0.3346   0.9489
   7.000   0.9997   0.01203   0.00564  -0.0124   0.3322   0.9499
   7.250   1.0252   0.01214   0.00580  -0.0123   0.3294   0.9508
   7.500   1.0498   0.01225   0.00596  -0.0120   0.3265   0.9517
   7.750   1.0737   0.01239   0.00611  -0.0115   0.3233   0.9527
   8.000   1.0968   0.01255   0.00628  -0.0110   0.3205   0.9539
   8.250   1.1201   0.01271   0.00648  -0.0105   0.3173   0.9551
   8.500   1.1441   0.01284   0.00667  -0.0101   0.3141   0.9564
   8.750   1.1671   0.01299   0.00686  -0.0096   0.3104   0.9579
   9.000   1.1888   0.01316   0.00707  -0.0089   0.3069   0.9595
   9.250   1.2087   0.01335   0.00727  -0.0078   0.3032   0.9615
   9.750   1.2514   0.01369   0.00774  -0.0062   0.2954   0.9656
  10.000   1.2709   0.01394   0.00801  -0.0052   0.2907   0.9680
  10.250   1.2925   0.01417   0.00831  -0.0046   0.2862   0.9703
  10.500   1.3130   0.01444   0.00862  -0.0039   0.2798   0.9731
  10.750   1.3332   0.01479   0.00899  -0.0033   0.2747   0.9760
  11.000   1.3572   0.01511   0.00938  -0.0034   0.2681   0.9785
  11.250   1.3783   0.01557   0.00986  -0.0032   0.2612   0.9819
  11.500   1.4015   0.01599   0.01034  -0.0035   0.2535   0.9856
  11.750   1.4224   0.01656   0.01093  -0.0036   0.2450   0.9917
  12.000   1.4373   0.01716   0.01156  -0.0026   0.2368   1.0000
  12.250   1.4476   0.01786   0.01228  -0.0009   0.2286   1.0000
  12.500   1.4544   0.01879   0.01321   0.0010   0.2197   1.0000
  12.750   1.4612   0.01982   0.01425   0.0026   0.2098   1.0000
  13.000   1.4665   0.02103   0.01548   0.0042   0.2013   1.0000
  13.250   1.4680   0.02259   0.01705   0.0057   0.1925   1.0000
  13.500   1.4706   0.02421   0.01871   0.0069   0.1839   1.0000
  13.750   1.4700   0.02618   0.02071   0.0080   0.1759   1.0000
  14.000   1.4662   0.02856   0.02310   0.0089   0.1678   1.0000
  14.250   1.4628   0.03103   0.02562   0.0096   0.1594   1.0000
  14.500   1.4562   0.03391   0.02853   0.0101   0.1531   1.0000
  14.750   1.4504   0.03682   0.03149   0.0105   0.1460   1.0000
  15.000   1.4391   0.04033   0.03504   0.0107   0.1394   1.0000
  15.250   1.4300   0.04374   0.03850   0.0108   0.1331   1.0000
  15.500   1.4166   0.04770   0.04250   0.0106   0.1273   1.0000
  15.750   1.4091   0.05116   0.04603   0.0103   0.1225   1.0000
  16.000   1.3961   0.05533   0.05024   0.0099   0.1174   1.0000
  16.250   1.3868   0.05920   0.05418   0.0093   0.1120   1.0000
  16.500   1.3746   0.06352   0.05854   0.0085   0.1067   1.0000
  16.750   1.3655   0.06754   0.06261   0.0077   0.1021   1.0000
  17.000   1.3562   0.07169   0.06681   0.0067   0.0973   1.0000
  17.250   1.3451   0.07615   0.07130   0.0056   0.0925   1.0000
  17.500   1.3377   0.08021   0.07541   0.0045   0.0876   1.0000
  17.750   1.3281   0.08463   0.07986   0.0032   0.0835   1.0000
  18.000   1.3232   0.08848   0.08377   0.0020   0.0793   1.0000
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