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EPPLER 548 AIRFOIL (e548-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 548 AIRFOIL (e548-il)
Reynolds number: 500,000
Max Cl/Cd: 93.68 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e548-il-500000.txt
Download as CSV file: xf-e548-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 548 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.3548   0.09472   0.09269  -0.0467   1.0000   0.0213
 -12.000  -0.3953   0.07902   0.07696  -0.0551   1.0000   0.0210
 -10.500  -0.7633   0.03756   0.03314  -0.0444   1.0000   0.0105
 -10.250  -0.7607   0.03645   0.03207  -0.0417   1.0000   0.0107
  -9.750  -0.7143   0.02823   0.02304  -0.0443   0.9541   0.0090
  -9.500  -0.6503   0.02444   0.01874  -0.0519   0.9365   0.0087
  -9.250  -0.5638   0.02207   0.01607  -0.0641   0.9056   0.0089
  -9.000  -0.5151   0.02096   0.01459  -0.0687   0.8439   0.0096
  -8.750  -0.4975   0.02035   0.01373  -0.0672   0.8048   0.0099
  -8.250  -0.4664   0.01922   0.01226  -0.0638   0.7545   0.0102
  -8.000  -0.4558   0.01831   0.01126  -0.0615   0.7357   0.0106
  -7.750  -0.4427   0.01770   0.01058  -0.0595   0.7191   0.0114
  -7.500  -0.4289   0.01716   0.00992  -0.0576   0.7043   0.0124
  -7.250  -0.4156   0.01662   0.00927  -0.0556   0.6907   0.0127
  -7.000  -0.4062   0.01593   0.00852  -0.0530   0.6780   0.0135
  -6.750  -0.3948   0.01543   0.00797  -0.0506   0.6669   0.0146
  -6.500  -0.3848   0.01504   0.00750  -0.0478   0.6569   0.0166
  -6.250  -0.3697   0.01468   0.00709  -0.0458   0.6472   0.0186
  -6.000  -0.3544   0.01425   0.00661  -0.0439   0.6387   0.0228
  -5.750  -0.3400   0.01371   0.00608  -0.0418   0.6302   0.0323
  -5.500  -0.3257   0.01314   0.00562  -0.0398   0.6230   0.0548
  -5.250  -0.3103   0.01256   0.00522  -0.0380   0.6155   0.0931
  -5.000  -0.2949   0.01197   0.00482  -0.0363   0.6089   0.1480
  -4.750  -0.2817   0.01108   0.00435  -0.0345   0.6023   0.2420
  -4.500  -0.2741   0.00966   0.00363  -0.0320   0.5963   0.4103
  -4.250  -0.2612   0.00874   0.00348  -0.0298   0.5908   0.6059
  -4.000  -0.2335   0.00893   0.00365  -0.0296   0.5850   0.6405
  -3.750  -0.2056   0.00922   0.00388  -0.0294   0.5795   0.6585
  -3.500  -0.1775   0.00948   0.00399  -0.0293   0.5745   0.6692
  -3.250  -0.1489   0.00968   0.00419  -0.0292   0.5696   0.6763
  -3.000  -0.1206   0.00993   0.00435  -0.0291   0.5647   0.6852
  -2.750  -0.0924   0.01030   0.00470  -0.0288   0.5601   0.6928
  -2.500  -0.0642   0.01071   0.00504  -0.0285   0.5558   0.7031
  -2.250  -0.0360   0.01123   0.00565  -0.0278   0.5517   0.7111
  -2.000  -0.0077   0.01146   0.00581  -0.0278   0.5478   0.7172
  -1.750   0.0207   0.01146   0.00568  -0.0281   0.5441   0.7193
  -1.500   0.0488   0.01138   0.00555  -0.0283   0.5407   0.7205
  -1.250   0.0771   0.01132   0.00546  -0.0286   0.5372   0.7217
  -1.000   0.1055   0.01127   0.00538  -0.0288   0.5336   0.7228
  -0.750   0.1339   0.01127   0.00532  -0.0291   0.5302   0.7239
  -0.500   0.1624   0.01130   0.00527  -0.0294   0.5271   0.7252
  -0.250   0.1910   0.01130   0.00523  -0.0297   0.5243   0.7263
   0.000   0.2196   0.01126   0.00518  -0.0301   0.5214   0.7274
   0.250   0.2482   0.01125   0.00514  -0.0304   0.5183   0.7288
   0.500   0.2768   0.01124   0.00509  -0.0308   0.5153   0.7302
   0.750   0.3055   0.01125   0.00504  -0.0312   0.5125   0.7314
   1.000   0.3345   0.01132   0.00504  -0.0317   0.5097   0.7325
   1.250   0.3632   0.01131   0.00502  -0.0321   0.5073   0.7336
   1.500   0.3919   0.01130   0.00501  -0.0325   0.5045   0.7347
   1.750   0.4205   0.01131   0.00500  -0.0329   0.5017   0.7359
   2.000   0.4488   0.01128   0.00497  -0.0332   0.4991   0.7370
   2.250   0.4772   0.01130   0.00497  -0.0335   0.4966   0.7379
   2.500   0.5059   0.01140   0.00504  -0.0340   0.4938   0.7389
   2.750   0.5341   0.01143   0.00510  -0.0342   0.4914   0.7398
   3.000   0.5622   0.01145   0.00516  -0.0345   0.4888   0.7409
   3.250   0.5905   0.01148   0.00520  -0.0348   0.4859   0.7419
   3.500   0.6187   0.01151   0.00525  -0.0351   0.4831   0.7430
   3.750   0.6471   0.01157   0.00530  -0.0354   0.4803   0.7442
   4.000   0.6759   0.01174   0.00542  -0.0359   0.4770   0.7456
   4.250   0.7033   0.01174   0.00549  -0.0360   0.4741   0.7471
   4.500   0.7310   0.01175   0.00555  -0.0363   0.4706   0.7484
   4.750   0.7590   0.01179   0.00560  -0.0365   0.4673   0.7497
   5.000   0.7870   0.01185   0.00565  -0.0368   0.4640   0.7508
   5.250   0.8155   0.01201   0.00579  -0.0373   0.4605   0.7519
   5.500   0.8420   0.01196   0.00584  -0.0372   0.4569   0.7531
   5.750   0.8689   0.01196   0.00590  -0.0373   0.4528   0.7543
   6.000   0.8959   0.01199   0.00596  -0.0373   0.4489   0.7555
   6.250   0.9235   0.01213   0.00609  -0.0376   0.4448   0.7568
   6.500   0.9493   0.01212   0.00620  -0.0374   0.4406   0.7582
   6.750   0.9756   0.01215   0.00629  -0.0373   0.4359   0.7597
   7.000   1.0019   0.01221   0.00637  -0.0373   0.4311   0.7615
   7.250   1.0278   0.01228   0.00651  -0.0372   0.4259   0.7632
   7.500   1.0534   0.01230   0.00661  -0.0370   0.4199   0.7649
   7.750   1.0789   0.01239   0.00669  -0.0369   0.4139   0.7665
   8.000   1.1042   0.01244   0.00685  -0.0367   0.4073   0.7680
   8.250   1.1285   0.01248   0.00693  -0.0363   0.3998   0.7696
   8.500   1.1527   0.01254   0.00708  -0.0359   0.3912   0.7712
   8.750   1.1753   0.01265   0.00723  -0.0352   0.3812   0.7729
   9.000   1.1974   0.01279   0.00741  -0.0345   0.3684   0.7748
   9.250   1.2179   0.01300   0.00764  -0.0335   0.3529   0.7768
   9.500   1.2367   0.01329   0.00793  -0.0322   0.3341   0.7790
   9.750   1.2512   0.01375   0.00832  -0.0303   0.3102   0.7813
  10.000   1.2616   0.01435   0.00883  -0.0278   0.2852   0.7838
  10.500   1.2679   0.01574   0.01008  -0.0204   0.2409   0.7891
  10.750   1.2699   0.01658   0.01088  -0.0168   0.2218   0.7919
  11.000   1.2694   0.01758   0.01183  -0.0132   0.2039   0.7951
  11.250   1.2680   0.01872   0.01292  -0.0098   0.1879   0.7985
  11.500   1.2660   0.02001   0.01419  -0.0068   0.1733   0.8018
  11.750   1.2632   0.02146   0.01566  -0.0042   0.1600   0.8055
  12.000   1.2599   0.02317   0.01738  -0.0019   0.1473   0.8095
  12.250   1.2563   0.02511   0.01932   0.0000   0.1353   0.8138
  12.500   1.2523   0.02724   0.02146   0.0015   0.1245   0.8182
  12.750   1.2471   0.02956   0.02381   0.0029   0.1148   0.8230
  13.000   1.2422   0.03199   0.02627   0.0040   0.1055   0.8288
  13.250   1.2390   0.03439   0.02871   0.0048   0.0969   0.8347
  13.500   1.2336   0.03699   0.03136   0.0057   0.0892   0.8415
  13.750   1.2289   0.03965   0.03405   0.0063   0.0818   0.8495
  14.000   1.2254   0.04219   0.03667   0.0069   0.0753   0.8593
  14.250   1.2184   0.04511   0.03965   0.0074   0.0690   0.8724
  14.750   1.2204   0.05074   0.04556   0.0057   0.0564   1.0000
  15.000   1.2174   0.05391   0.04872   0.0052   0.0515   1.0000
  15.250   1.2173   0.05682   0.05168   0.0047   0.0472   1.0000
  15.500   1.2130   0.06025   0.05510   0.0041   0.0429   1.0000
  15.750   1.2143   0.06309   0.05799   0.0034   0.0396   1.0000
  16.000   1.2102   0.06665   0.06156   0.0026   0.0365   1.0000
  16.250   1.2114   0.06962   0.06457   0.0019   0.0333   1.0000
  16.500   1.2082   0.07320   0.06818   0.0009   0.0309   1.0000
  16.750   1.2080   0.07647   0.07151   0.0000   0.0286   1.0000
  17.000   1.2066   0.07995   0.07503  -0.0011   0.0264   1.0000
  17.250   1.2010   0.08407   0.07918  -0.0024   0.0250   1.0000
  17.500   1.2036   0.08712   0.08232  -0.0035   0.0228   1.0000
  17.750   1.1999   0.09114   0.08638  -0.0050   0.0214   1.0000
  18.000   1.1992   0.09478   0.09009  -0.0064   0.0199   1.0000
  18.250   1.1973   0.09864   0.09403  -0.0079   0.0186   1.0000
  18.500   1.1907   0.10329   0.09872  -0.0098   0.0175   1.0000
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