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EPPLER 604 AIRFOIL (e604-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 604 AIRFOIL (e604-il)
Reynolds number: 50,000
Max Cl/Cd: 5.18 at α=12°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e604-il-50000.txt
Download as CSV file: xf-e604-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 604 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.6387   0.09930   0.09416  -0.0404   1.0000   0.1387
  -8.500  -0.6387   0.09519   0.09005  -0.0392   1.0000   0.1310
  -8.250  -0.6881   0.09139   0.08622  -0.0369   1.0000   0.1274
  -8.000  -0.7623   0.08626   0.08056  -0.0351   1.0000   0.1213
  -7.750  -0.7538   0.08203   0.07642  -0.0338   1.0000   0.1175
  -7.500  -0.7688   0.07738   0.07152  -0.0324   1.0000   0.1134
  -7.250  -0.7911   0.07167   0.06492  -0.0313   1.0000   0.1062
  -7.000  -0.7865   0.06781   0.06086  -0.0302   1.0000   0.1049
  -6.750  -0.7820   0.06403   0.05668  -0.0292   1.0000   0.1046
  -6.500  -0.7739   0.06048   0.05267  -0.0284   1.0000   0.1048
  -6.250  -0.7619   0.05732   0.04902  -0.0277   1.0000   0.1053
  -6.000  -0.7469   0.05433   0.04548  -0.0270   1.0000   0.1064
  -5.750  -0.7297   0.05165   0.04233  -0.0262   1.0000   0.1076
  -5.500  -0.7132   0.04939   0.04018  -0.0254   1.0000   0.1129
  -5.250  -0.6942   0.04756   0.03802  -0.0246   1.0000   0.1183
  -5.000  -0.6746   0.04565   0.03584  -0.0236   1.0000   0.1246
  -4.750  -0.6555   0.04432   0.03440  -0.0224   1.0000   0.1349
  -4.500  -0.6369   0.04304   0.03319  -0.0209   1.0000   0.1466
  -4.250  -0.6186   0.04205   0.03228  -0.0189   1.0000   0.1623
  -4.000  -0.6010   0.04123   0.03151  -0.0168   1.0000   0.1851
  -3.750  -0.5862   0.04011   0.03080  -0.0146   1.0000   0.2195
  -3.500  -0.5715   0.03773   0.02952  -0.0138   1.0000   0.3080
  -3.250  -0.5867   0.03975   0.03385   0.0005   1.0000   0.6462
  -3.000  -0.5935   0.04295   0.03687   0.0125   1.0000   0.7101
  -2.750  -0.5973   0.04506   0.03884   0.0228   1.0000   0.7481
  -2.500  -0.5974   0.04654   0.04017   0.0317   1.0000   0.7834
  -2.250  -0.5920   0.04769   0.04112   0.0389   1.0000   0.8172
  -2.000  -0.5769   0.04884   0.04203   0.0439   1.0000   0.8521
  -1.750  -0.2672   0.05885   0.05065  -0.0002   1.0000   0.9649
  -1.500  -0.2197   0.05954   0.05104  -0.0070   1.0000   0.9802
  -1.250  -0.1787   0.06015   0.05143  -0.0127   1.0000   0.9910
  -1.000  -0.1433   0.06093   0.05199  -0.0175   1.0000   0.9996
  -0.750  -0.1378   0.06092   0.05188  -0.0163   1.0000   1.0000
  -0.500  -0.1341   0.06087   0.05174  -0.0147   1.0000   1.0000
  -0.250  -0.1305   0.06084   0.05162  -0.0131   1.0000   1.0000
   0.000  -0.1267   0.06083   0.05153  -0.0115   1.0000   1.0000
   0.250  -0.1230   0.06083   0.05144  -0.0098   1.0000   1.0000
   0.500  -0.1194   0.06084   0.05139  -0.0082   1.0000   1.0000
   0.750  -0.1159   0.06086   0.05134  -0.0065   1.0000   1.0000
   1.000  -0.1125   0.06088   0.05129  -0.0048   1.0000   1.0000
   1.250  -0.1092   0.06091   0.05127  -0.0032   1.0000   1.0000
   1.500  -0.1060   0.06093   0.05122  -0.0014   1.0000   1.0000
   1.750  -0.0943   0.06125   0.05149  -0.0015   0.9972   1.0000
   2.000  -0.0688   0.06229   0.05246  -0.0042   0.9878   1.0000
   2.250  -0.0475   0.06326   0.05337  -0.0061   0.9780   1.0000
   2.500  -0.0274   0.06439   0.05443  -0.0077   0.9684   1.0000
   2.750  -0.0056   0.06569   0.05567  -0.0095   0.9573   1.0000
   3.000   0.0069   0.06590   0.05585  -0.0094   0.9453   1.0000
   3.250   0.0175   0.06631   0.05623  -0.0090   0.9342   1.0000
   3.500   0.0319   0.06744   0.05731  -0.0093   0.9255   1.0000
   3.750   0.0472   0.06827   0.05812  -0.0096   0.9130   1.0000
   4.000   0.0509   0.06816   0.05799  -0.0079   0.9012   1.0000
   4.250   0.0611   0.06909   0.05889  -0.0074   0.8925   1.0000
   4.500   0.0751   0.06994   0.05972  -0.0074   0.8804   1.0000
   4.750   0.0757   0.06970   0.05948  -0.0052   0.8689   1.0000
   5.000   0.0932   0.07141   0.06115  -0.0060   0.8611   1.0000
   5.250   0.1065   0.07195   0.06169  -0.0060   0.8482   1.0000
   5.500   0.1164   0.07263   0.06237  -0.0059   0.8378   1.0000
   5.750   0.1537   0.07599   0.06571  -0.0101   0.8294   1.0000
   6.000   0.1607   0.07601   0.06575  -0.0096   0.8167   1.0000
   6.250   0.1784   0.07766   0.06742  -0.0110   0.8074   1.0000
   6.500   0.2147   0.08076   0.07053  -0.0151   0.7969   1.0000
   6.750   0.2236   0.08142   0.07123  -0.0152   0.7846   1.0000
   7.000   0.2446   0.08361   0.07345  -0.0172   0.7755   1.0000
   7.250   0.2802   0.08677   0.07665  -0.0211   0.7641   1.0000
   7.500   0.2883   0.08767   0.07760  -0.0213   0.7516   1.0000
   7.750   0.3068   0.08989   0.07987  -0.0231   0.7415   1.0000
   8.000   0.3489   0.09395   0.08398  -0.0278   0.7307   1.0000
   8.250   0.3536   0.09468   0.08478  -0.0277   0.7175   1.0000
   8.500   0.3663   0.09670   0.08687  -0.0289   0.7067   1.0000
   8.750   0.3980   0.10024   0.09046  -0.0322   0.6967   1.0000
   9.000   0.4199   0.10256   0.09288  -0.0342   0.6830   1.0000
   9.250   0.4255   0.10416   0.09454  -0.0346   0.6707   1.0000
   9.500   0.4417   0.10684   0.09730  -0.0363   0.6604   1.0000
   9.750   0.4753   0.11060   0.10114  -0.0396   0.6488   1.0000
  10.000   0.4903   0.11267   0.10331  -0.0408   0.6347   1.0000
  10.250   0.4929   0.11459   0.10531  -0.0413   0.6234   1.0000
  10.500   0.5100   0.11763   0.10842  -0.0431   0.6133   1.0000
  10.750   0.5398   0.12123   0.11214  -0.0457   0.6006   1.0000
  11.000   0.5602   0.12391   0.11492  -0.0473   0.5860   1.0000
  11.250   0.5541   0.12568   0.11675  -0.0475   0.5757   1.0000
  11.500   0.6324   0.12311   0.11429  -0.0472   0.5063   1.0000
  11.750   0.6326   0.12739   0.11867  -0.0490   0.5061   1.0000
  12.000   0.6577   0.12691   0.11827  -0.0485   0.4715   1.0000
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