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EPPLER EA 6(-1)-009 AIRFOIL (ea61009-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER EA 6(-1)-009 AIRFOIL (ea61009-il)
Reynolds number: 100,000
Max Cl/Cd: 27.23 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ea61009-il-100000-n5.txt
Download as CSV file: xf-ea61009-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER EA 6(-1)-009 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.7793   0.08372   0.07875  -0.0031   1.0000   0.0379
 -10.750  -0.8071   0.07416   0.06911  -0.0108   1.0000   0.0373
 -10.500  -0.8331   0.06742   0.06225  -0.0152   1.0000   0.0370
 -10.250  -0.8589   0.06220   0.05686  -0.0168   1.0000   0.0369
 -10.000  -0.8807   0.05753   0.05190  -0.0165   1.0000   0.0374
  -9.750  -0.8974   0.05249   0.04634  -0.0158   1.0000   0.0385
  -9.500  -0.8996   0.04863   0.04209  -0.0151   1.0000   0.0400
  -9.250  -0.8842   0.04714   0.04062  -0.0149   1.0000   0.0420
  -9.000  -0.8723   0.04488   0.03816  -0.0143   1.0000   0.0441
  -8.750  -0.8626   0.04175   0.03459  -0.0136   1.0000   0.0462
  -8.500  -0.8514   0.03897   0.03115  -0.0126   1.0000   0.0494
  -8.250  -0.8360   0.03654   0.02817  -0.0119   1.0000   0.0520
  -8.000  -0.8152   0.03465   0.02619  -0.0117   1.0000   0.0539
  -7.750  -0.7944   0.03299   0.02426  -0.0113   1.0000   0.0569
  -7.500  -0.7737   0.03130   0.02204  -0.0106   1.0000   0.0598
  -7.250  -0.7505   0.02944   0.01989  -0.0101   1.0000   0.0611
  -7.000  -0.7259   0.02778   0.01816  -0.0099   1.0000   0.0624
  -6.750  -0.7010   0.02641   0.01668  -0.0096   1.0000   0.0640
  -6.500  -0.6759   0.02518   0.01531  -0.0093   1.0000   0.0656
  -6.250  -0.6505   0.02410   0.01403  -0.0089   1.0000   0.0671
  -6.000  -0.6250   0.02316   0.01292  -0.0086   1.0000   0.0685
  -5.750  -0.6005   0.02205   0.01191  -0.0083   1.0000   0.0708
  -5.500  -0.5759   0.02119   0.01106  -0.0079   1.0000   0.0737
  -5.250  -0.5512   0.02042   0.01022  -0.0075   1.0000   0.0758
  -5.000  -0.5267   0.01970   0.00945  -0.0070   1.0000   0.0769
  -4.750  -0.5036   0.01888   0.00870  -0.0064   1.0000   0.0782
  -4.500  -0.4807   0.01819   0.00804  -0.0057   1.0000   0.0797
  -4.250  -0.4580   0.01760   0.00746  -0.0051   1.0000   0.0815
  -4.000  -0.4359   0.01709   0.00691  -0.0042   1.0000   0.0836
  -3.750  -0.4147   0.01666   0.00644  -0.0032   1.0000   0.0858
  -3.500  -0.3953   0.01620   0.00600  -0.0020   1.0000   0.0887
  -3.250  -0.3765   0.01580   0.00563  -0.0007   1.0000   0.0939
  -3.000  -0.3550   0.01537   0.00528   0.0000   0.9979   0.1034
  -2.750  -0.3223   0.01471   0.00499  -0.0016   0.9883   0.1508
  -2.500  -0.2904   0.01383   0.00468  -0.0032   0.9800   0.2669
  -2.250  -0.2594   0.01285   0.00450  -0.0046   0.9727   0.4401
  -2.000  -0.2311   0.01235   0.00463  -0.0046   0.9641   0.5750
  -1.750  -0.2005   0.01226   0.00488  -0.0045   0.9569   0.6684
  -1.500  -0.1706   0.01234   0.00511  -0.0043   0.9488   0.7268
  -1.250  -0.1397   0.01245   0.00526  -0.0044   0.9403   0.7643
  -1.000  -0.1079   0.01255   0.00537  -0.0046   0.9312   0.7907
  -0.750  -0.0789   0.01264   0.00547  -0.0042   0.9203   0.8119
  -0.500  -0.0502   0.01273   0.00557  -0.0035   0.9089   0.8325
  -0.250  -0.0245   0.01281   0.00567  -0.0020   0.8951   0.8560
   0.000   0.0000   0.01283   0.00571   0.0000   0.8767   0.8765
   0.250   0.0245   0.01281   0.00567   0.0020   0.8562   0.8949
   0.500   0.0503   0.01273   0.00557   0.0035   0.8327   0.9088
   0.750   0.0789   0.01264   0.00547   0.0042   0.8118   0.9203
   1.000   0.1079   0.01256   0.00537   0.0046   0.7909   0.9312
   1.250   0.1397   0.01245   0.00526   0.0044   0.7643   0.9403
   1.500   0.1707   0.01234   0.00511   0.0043   0.7273   0.9488
   2.000   0.2312   0.01235   0.00463   0.0045   0.5768   0.9641
   2.250   0.2594   0.01285   0.00450   0.0046   0.4401   0.9727
   2.500   0.2904   0.01382   0.00468   0.0032   0.2677   0.9799
   2.750   0.3223   0.01471   0.00499   0.0016   0.1512   0.9882
   3.000   0.3550   0.01537   0.00528   0.0000   0.1034   0.9978
   3.250   0.3766   0.01579   0.00563   0.0007   0.0941   1.0000
   3.500   0.3954   0.01620   0.00601   0.0020   0.0887   1.0000
   3.750   0.4148   0.01666   0.00644   0.0032   0.0858   1.0000
   4.000   0.4360   0.01709   0.00691   0.0042   0.0836   1.0000
   4.250   0.4581   0.01760   0.00745   0.0050   0.0815   1.0000
   4.500   0.4807   0.01819   0.00804   0.0057   0.0797   1.0000
   4.750   0.5036   0.01888   0.00870   0.0064   0.0782   1.0000
   5.000   0.5267   0.01970   0.00945   0.0070   0.0769   1.0000
   5.250   0.5511   0.02042   0.01022   0.0075   0.0759   1.0000
   5.500   0.5759   0.02119   0.01106   0.0080   0.0738   1.0000
   5.750   0.6004   0.02205   0.01191   0.0083   0.0708   1.0000
   6.000   0.6249   0.02316   0.01292   0.0086   0.0685   1.0000
   6.250   0.6504   0.02409   0.01402   0.0090   0.0671   1.0000
   6.500   0.6758   0.02518   0.01531   0.0093   0.0656   1.0000
   6.750   0.7009   0.02640   0.01667   0.0096   0.0640   1.0000
   7.000   0.7258   0.02778   0.01815   0.0099   0.0624   1.0000
   7.250   0.7503   0.02943   0.01988   0.0102   0.0611   1.0000
   7.500   0.7735   0.03129   0.02203   0.0106   0.0598   1.0000
   7.750   0.7941   0.03296   0.02424   0.0113   0.0568   1.0000
   8.000   0.8149   0.03464   0.02618   0.0117   0.0539   1.0000
   8.250   0.8357   0.03652   0.02816   0.0120   0.0520   1.0000
   8.500   0.8511   0.03895   0.03113   0.0127   0.0495   1.0000
   8.750   0.8623   0.04174   0.03457   0.0137   0.0462   1.0000
   9.000   0.8720   0.04485   0.03812   0.0144   0.0441   1.0000
   9.250   0.8836   0.04717   0.04066   0.0150   0.0420   1.0000
   9.500   0.8987   0.04871   0.04219   0.0152   0.0401   1.0000
   9.750   0.8970   0.05245   0.04630   0.0159   0.0385   1.0000
  10.000   0.8798   0.05751   0.05190   0.0166   0.0373   1.0000
  10.250   0.8586   0.06216   0.05682   0.0169   0.0369   1.0000
  10.500   0.8336   0.06731   0.06214   0.0153   0.0370   1.0000
  10.750   0.8061   0.07429   0.06925   0.0107   0.0373   1.0000
  11.000   0.7795   0.08365   0.07868   0.0032   0.0379   1.0000
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