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EPPLER 344 AIRFOIL (e344-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 344 AIRFOIL (e344-il)
Reynolds number: 100,000
Max Cl/Cd: 31.46 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e344-il-100000.txt
Download as CSV file: xf-e344-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2593   0.09986   0.09563  -0.0369   1.0000   0.0805
  -8.750  -0.2714   0.09734   0.09324  -0.0394   1.0000   0.0822
  -8.500  -0.2943   0.09491   0.09099  -0.0426   1.0000   0.0829
  -8.250  -0.3184   0.09368   0.08998  -0.0410   1.0000   0.0830
  -8.000  -0.3289   0.09025   0.08631  -0.0529   0.9636   0.0837
  -7.750  -0.2653   0.08258   0.07896  -0.0497   0.9643   0.0881
  -7.500  -0.2400   0.07730   0.07361  -0.0574   0.9364   0.0930
  -7.250  -0.2482   0.07457   0.07025  -0.0688   0.9026   0.0987
  -7.000  -0.2046   0.06657   0.06246  -0.0719   0.8832   0.1023
  -6.750  -0.1822   0.06318   0.05891  -0.0738   0.8562   0.1078
  -6.500  -0.1997   0.06355   0.05854  -0.0732   0.8309   0.1153
  -6.250  -0.1726   0.05744   0.05267  -0.0738   0.8106   0.1190
  -6.000  -0.1600   0.05521   0.05029  -0.0728   0.7913   0.1256
  -5.750  -0.1587   0.05297   0.04774  -0.0713   0.7752   0.1348
  -5.500  -0.1435   0.05067   0.04538  -0.0700   0.7593   0.1416
  -5.250  -0.1362   0.04848   0.04296  -0.0683   0.7459   0.1537
  -5.000  -0.1271   0.04663   0.04088  -0.0664   0.7330   0.1696
  -4.750  -0.1164   0.04475   0.03889  -0.0645   0.7198   0.1869
  -4.500  -0.1032   0.04272   0.03682  -0.0626   0.7083   0.2064
  -4.000  -0.0791   0.03919   0.03320  -0.0582   0.6867   0.2622
  -3.750  -0.0667   0.03733   0.03128  -0.0558   0.6777   0.2941
  -3.500  -0.0023   0.03241   0.02395  -0.0554   0.6697   0.0804
  -3.250   0.0244   0.03115   0.02190  -0.0531   0.6619   0.0705
  -3.000   0.0489   0.02905   0.01965  -0.0522   0.6520   0.0688
  -2.750   0.0772   0.02735   0.01766  -0.0515   0.6448   0.0668
  -2.500   0.1040   0.02611   0.01626  -0.0507   0.6353   0.0660
  -2.250   0.1350   0.02494   0.01481  -0.0503   0.6287   0.0674
  -2.000   0.1611   0.02414   0.01395  -0.0496   0.6195   0.0715
  -1.750   0.4291   0.01986   0.01221  -0.0864   0.6025   1.0000
  -1.500   0.4504   0.01994   0.01200  -0.0855   0.5963   1.0000
  -1.250   0.4710   0.02011   0.01202  -0.0846   0.5896   1.0000
  -1.000   0.4919   0.02025   0.01200  -0.0836   0.5828   1.0000
  -0.750   0.5141   0.02040   0.01190  -0.0828   0.5779   1.0000
  -0.500   0.5342   0.02069   0.01215  -0.0819   0.5717   1.0000
  -0.250   0.5554   0.02091   0.01226  -0.0810   0.5660   1.0000
   0.000   0.5779   0.02111   0.01226  -0.0802   0.5616   1.0000
   0.250   0.5978   0.02146   0.01259  -0.0793   0.5559   1.0000
   0.500   0.6185   0.02177   0.01284  -0.0783   0.5504   1.0000
   0.750   0.6408   0.02202   0.01296  -0.0775   0.5462   1.0000
   1.000   0.6623   0.02239   0.01324  -0.0767   0.5423   1.0000
   1.250   0.6807   0.02290   0.01381  -0.0755   0.5368   1.0000
   1.500   0.7016   0.02325   0.01411  -0.0746   0.5322   1.0000
   1.750   0.7243   0.02351   0.01425  -0.0738   0.5285   1.0000
   2.000   0.7433   0.02409   0.01484  -0.0727   0.5243   1.0000
   2.250   0.7602   0.02478   0.01561  -0.0714   0.5195   1.0000
   2.500   0.7804   0.02522   0.01601  -0.0703   0.5154   1.0000
   2.750   0.8028   0.02552   0.01623  -0.0695   0.5119   1.0000
   3.000   0.8203   0.02623   0.01697  -0.0681   0.5081   1.0000
   3.250   0.8326   0.02725   0.01813  -0.0663   0.5033   1.0000
   3.500   0.8502   0.02789   0.01878  -0.0649   0.4994   1.0000
   3.750   0.8723   0.02823   0.01906  -0.0640   0.4961   1.0000
   4.000   0.8941   0.02870   0.01947  -0.0631   0.4930   1.0000
   4.250   0.8948   0.03042   0.02146  -0.0599   0.4878   1.0000
   4.500   0.9066   0.03141   0.02252  -0.0579   0.4835   1.0000
   4.750   0.9275   0.03180   0.02288  -0.0568   0.4802   1.0000
   5.000   0.9536   0.03198   0.02297  -0.0563   0.4775   1.0000
   5.250   0.9391   0.03460   0.02587  -0.0515   0.4720   1.0000
   5.500   0.9375   0.03633   0.02772  -0.0480   0.4673   1.0000
   5.750   0.9573   0.03670   0.02810  -0.0467   0.4640   1.0000
   6.000   0.9898   0.03647   0.02779  -0.0468   0.4616   1.0000
   6.250   0.8948   0.04346   0.03517  -0.0338   0.4532   1.0000
   6.500   0.8772   0.04575   0.03751  -0.0288   0.4485   1.0000
   6.750   0.9295   0.04423   0.03594  -0.0304   0.4464   1.0000
   7.000   0.9872   0.04267   0.03432  -0.0330   0.4448   1.0000
   7.250   0.6731   0.06449   0.05627  -0.0093   0.4288   1.0000
   7.500   0.5902   0.07439   0.06619  -0.0084   0.4235   1.0000
   7.750   0.5739   0.07861   0.07044  -0.0082   0.4208   1.0000
   8.000   0.6181   0.07725   0.06907  -0.0072   0.4140   1.0000
   8.250   0.6176   0.08029   0.07212  -0.0068   0.4098   1.0000
   8.500   0.5953   0.08553   0.07741  -0.0073   0.4086   1.0000
   8.750   0.5881   0.08966   0.08157  -0.0078   0.4087   1.0000
   9.000   0.5981   0.09296   0.08490  -0.0083   0.4104   1.0000
   9.250   0.6160   0.09591   0.08789  -0.0088   0.4114   1.0000
   9.500   0.6172   0.09640   0.08837  -0.0075   0.3941   1.0000
   9.750   0.6304   0.09966   0.09168  -0.0081   0.3952   1.0000
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