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EPPLER 908 AIRFOIL (e908-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 908 AIRFOIL (e908-il)
Reynolds number: 200,000
Max Cl/Cd: 47.82 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e908-il-200000.txt
Download as CSV file: xf-e908-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 908 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.5143   0.09375   0.09068  -0.0259   1.0000   0.0291
  -7.500  -0.5250   0.09104   0.08802  -0.0249   1.0000   0.0296
  -7.250  -0.5397   0.08858   0.08561  -0.0237   1.0000   0.0296
  -7.000  -0.5509   0.08543   0.08251  -0.0240   1.0000   0.0298
  -6.750  -0.5571   0.08121   0.07831  -0.0265   1.0000   0.0300
  -6.500  -0.5603   0.07670   0.07379  -0.0290   1.0000   0.0308
  -6.250  -0.5601   0.07215   0.06919  -0.0313   1.0000   0.0317
  -6.000  -0.5566   0.06743   0.06438  -0.0336   1.0000   0.0327
  -5.750  -0.5485   0.06220   0.05898  -0.0363   1.0000   0.0348
  -5.500  -0.5284   0.05836   0.05452  -0.0396   1.0000   0.0376
  -5.250  -0.5233   0.05054   0.04668  -0.0414   1.0000   0.0394
  -5.000  -0.5103   0.04772   0.04385  -0.0412   1.0000   0.0419
  -4.750  -0.4867   0.04373   0.03906  -0.0432   1.0000   0.0512
  -4.500  -0.4722   0.04095   0.03635  -0.0436   1.0000   0.0656
  -4.250  -0.4355   0.03820   0.03346  -0.0475   0.9959   0.0805
  -3.750  -0.3478   0.02741   0.02081  -0.0504   0.9904   0.0359
  -3.500  -0.3099   0.02443   0.01714  -0.0510   0.9878   0.0266
  -3.250  -0.2735   0.02298   0.01546  -0.0524   0.9851   0.0244
  -3.000  -0.2364   0.02134   0.01361  -0.0539   0.9832   0.0233
  -2.750  -0.2057   0.02011   0.01229  -0.0544   0.9788   0.0230
  -2.500  -0.1723   0.01927   0.01132  -0.0556   0.9751   0.0238
  -2.250  -0.1352   0.01853   0.01036  -0.0574   0.9724   0.0368
  -2.000  -0.1088   0.01604   0.01062  -0.0582   0.9712   0.6692
  -1.750  -0.0897   0.01599   0.01083  -0.0558   0.9651   0.7749
  -1.500  -0.0621   0.01612   0.01094  -0.0554   0.9608   0.8172
  -1.250  -0.0311   0.01632   0.01107  -0.0559   0.9571   0.8451
  -1.000  -0.0090   0.01623   0.01095  -0.0548   0.9506   0.8703
  -0.750   0.0236   0.01634   0.01102  -0.0557   0.9471   0.8982
  -0.500   0.0587   0.01638   0.01099  -0.0574   0.9429   0.9357
  -0.250   0.1013   0.01638   0.01091  -0.0612   0.9382   1.0000
   0.000   0.1398   0.01658   0.01101  -0.0640   0.9349   1.0000
   0.250   0.1808   0.01685   0.01119  -0.0673   0.9327   1.0000
   0.500   0.2041   0.01687   0.01116  -0.0670   0.9246   1.0000
   0.750   0.2426   0.01704   0.01129  -0.0697   0.9215   1.0000
   1.000   0.2707   0.01718   0.01139  -0.0702   0.9152   1.0000
   1.250   0.3046   0.01730   0.01150  -0.0719   0.9105   1.0000
   1.500   0.3438   0.01742   0.01163  -0.0745   0.9079   1.0000
   1.750   0.3679   0.01754   0.01177  -0.0742   0.9000   1.0000
   2.000   0.4046   0.01762   0.01194  -0.0763   0.8964   1.0000
   2.250   0.4411   0.01768   0.01208  -0.0783   0.8928   1.0000
   2.500   0.4672   0.01775   0.01221  -0.0783   0.8849   1.0000
   2.750   0.5075   0.01770   0.01227  -0.0808   0.8821   1.0000
   3.000   0.5322   0.01776   0.01244  -0.0804   0.8733   1.0000
   3.250   0.5728   0.01758   0.01253  -0.0828   0.8699   1.0000
   3.500   0.6595   0.01379   0.00525  -0.0847   0.1108   1.0000
   3.750   0.6693   0.01531   0.00640  -0.0811   0.0273   1.0000
   4.000   0.6868   0.01618   0.00744  -0.0789   0.0248   1.0000
   4.250   0.7030   0.01724   0.00860  -0.0764   0.0236   1.0000
   4.500   0.7220   0.01847   0.00988  -0.0746   0.0213   1.0000
   4.750   0.7502   0.02090   0.01227  -0.0750   0.0157   1.0000
   5.000   0.7928   0.02369   0.01516  -0.0772   0.0157   1.0000
   5.250   0.8261   0.02511   0.01687  -0.0773   0.0170   1.0000
   5.750   0.9290   0.03532   0.02854  -0.0768   0.0686   1.0000
   6.000   0.9420   0.03782   0.03129  -0.0744   0.0578   1.0000
   6.250   0.9600   0.04090   0.03442  -0.0731   0.0530   1.0000
   6.500   0.9666   0.04320   0.03723  -0.0690   0.0457   1.0000
   6.750   0.9791   0.04590   0.04012  -0.0667   0.0420   1.0000
   7.000   0.9936   0.05076   0.04490  -0.0661   0.0396   1.0000
   7.250   0.9888   0.05701   0.05152  -0.0622   0.0381   1.0000
   7.500   0.9942   0.05551   0.05064  -0.0564   0.0337   1.0000
   7.750   0.9969   0.05858   0.05396  -0.0531   0.0316   1.0000
   8.000   0.9978   0.06173   0.05729  -0.0501   0.0302   1.0000
   8.250   0.9978   0.06501   0.06070  -0.0474   0.0290   1.0000
   8.500   0.9971   0.06879   0.06454  -0.0452   0.0281   1.0000
  10.500   0.7424   0.10516   0.10238  -0.0362   0.0328   1.0000
  10.750   0.7308   0.11216   0.10936  -0.0403   0.0329   1.0000
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