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EPPLER 548 AIRFOIL (e548-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 548 AIRFOIL (e548-il)
Reynolds number: 100,000
Max Cl/Cd: 38.56 at α=9.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e548-il-100000-n5.txt
Download as CSV file: xf-e548-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.4937   0.09321   0.08807  -0.0496   1.0000   0.0190
 -12.500  -0.5139   0.08546   0.08026  -0.0543   1.0000   0.0188
 -12.250  -0.5340   0.07914   0.07385  -0.0576   1.0000   0.0186
 -12.000  -0.5566   0.07342   0.06800  -0.0599   1.0000   0.0184
 -11.750  -0.5773   0.06860   0.06305  -0.0609   1.0000   0.0183
 -11.500  -0.6013   0.06391   0.05817  -0.0611   1.0000   0.0183
 -11.250  -0.6180   0.06033   0.05443  -0.0603   1.0000   0.0182
 -11.000  -0.6350   0.05695   0.05086  -0.0588   1.0000   0.0181
 -10.750  -0.6513   0.05381   0.04751  -0.0566   1.0000   0.0181
 -10.500  -0.6633   0.05122   0.04474  -0.0540   1.0000   0.0180
 -10.250  -0.6758   0.04869   0.04199  -0.0507   1.0000   0.0181
 -10.000  -0.6854   0.04658   0.03969  -0.0470   1.0000   0.0181
  -9.750  -0.6939   0.04453   0.03744  -0.0430   1.0000   0.0182
  -9.500  -0.6972   0.04249   0.03517  -0.0394   1.0000   0.0183
  -9.250  -0.6783   0.03951   0.03182  -0.0397   0.9808   0.0186
  -9.000  -0.6461   0.03636   0.02816  -0.0415   0.9551   0.0191
  -8.750  -0.6038   0.03402   0.02567  -0.0452   0.9333   0.0199
  -8.500  -0.5546   0.03188   0.02332  -0.0497   0.9118   0.0211
  -8.250  -0.5046   0.03001   0.02117  -0.0540   0.8881   0.0234
  -8.000  -0.4624   0.02862   0.01961  -0.0572   0.8612   0.0264
  -7.750  -0.4301   0.02733   0.01818  -0.0584   0.8350   0.0286
  -7.500  -0.4058   0.02636   0.01700  -0.0582   0.8115   0.0321
  -7.250  -0.3871   0.02551   0.01608  -0.0574   0.7913   0.0357
  -7.000  -0.3706   0.02468   0.01514  -0.0560   0.7736   0.0405
  -6.750  -0.3552   0.02388   0.01427  -0.0544   0.7585   0.0479
  -6.500  -0.3411   0.02311   0.01348  -0.0526   0.7448   0.0595
  -6.250  -0.3280   0.02237   0.01283  -0.0505   0.7321   0.0783
  -6.000  -0.3161   0.02161   0.01225  -0.0484   0.7209   0.1146
  -5.750  -0.3086   0.02070   0.01168  -0.0457   0.7105   0.1782
  -5.500  -0.3108   0.01949   0.01101  -0.0418   0.7006   0.2741
  -5.250  -0.2851   0.02074   0.01393  -0.0369   0.6924   0.5536
  -5.000  -0.2829   0.02033   0.01336  -0.0336   0.6833   0.6058
  -4.750  -0.2735   0.02032   0.01311  -0.0308   0.6760   0.6385
  -4.500  -0.2460   0.02140   0.01402  -0.0292   0.6677   0.6602
  -4.250  -0.2186   0.02228   0.01468  -0.0277   0.6605   0.6768
  -4.000  -0.1874   0.02345   0.01569  -0.0264   0.6531   0.6933
  -3.750  -0.1510   0.02482   0.01688  -0.0254   0.6459   0.7094
  -3.500  -0.1273   0.02516   0.01704  -0.0240   0.6402   0.7215
  -3.250  -0.0979   0.02525   0.01699  -0.0239   0.6335   0.7251
  -3.000  -0.0766   0.02507   0.01663  -0.0231   0.6282   0.7306
  -2.750  -0.0614   0.02468   0.01608  -0.0217   0.6234   0.7370
  -2.500  -0.0344   0.02463   0.01593  -0.0215   0.6174   0.7393
  -2.250  -0.0090   0.02453   0.01567  -0.0212   0.6121   0.7423
  -2.000   0.0129   0.02431   0.01530  -0.0206   0.6081   0.7462
  -1.750   0.0250   0.02384   0.01476  -0.0191   0.6029   0.7524
  -1.500   0.0515   0.02378   0.01461  -0.0189   0.5983   0.7541
  -1.250   0.0775   0.02369   0.01440  -0.0188   0.5943   0.7560
  -1.000   0.1024   0.02358   0.01418  -0.0185   0.5906   0.7583
  -0.750   0.1243   0.02345   0.01401  -0.0180   0.5857   0.7612
  -0.500   0.1455   0.02325   0.01373  -0.0175   0.5814   0.7642
  -0.250   0.1654   0.02295   0.01332  -0.0171   0.5778   0.7683
   0.000   0.1918   0.02289   0.01316  -0.0171   0.5749   0.7698
   0.250   0.2154   0.02286   0.01315  -0.0167   0.5707   0.7712
   0.500   0.2397   0.02284   0.01311  -0.0165   0.5666   0.7730
   0.750   0.2646   0.02280   0.01302  -0.0163   0.5630   0.7751
   1.000   0.2901   0.02274   0.01288  -0.0163   0.5600   0.7771
   1.250   0.3141   0.02270   0.01282  -0.0162   0.5566   0.7791
   1.500   0.3368   0.02269   0.01284  -0.0161   0.5528   0.7814
   1.750   0.3607   0.02266   0.01278  -0.0162   0.5492   0.7843
   2.000   0.3863   0.02267   0.01278  -0.0161   0.5459   0.7859
   2.250   0.4132   0.02268   0.01275  -0.0163   0.5432   0.7872
   2.500   0.4373   0.02279   0.01291  -0.0161   0.5399   0.7886
   2.750   0.4603   0.02292   0.01311  -0.0158   0.5360   0.7903
   3.000   0.4848   0.02302   0.01323  -0.0157   0.5324   0.7921
   3.250   0.5106   0.02308   0.01330  -0.0158   0.5293   0.7942
   3.500   0.5380   0.02314   0.01335  -0.0161   0.5267   0.7964
   3.750   0.5616   0.02333   0.01360  -0.0161   0.5231   0.7987
   4.000   0.5846   0.02353   0.01389  -0.0161   0.5189   0.8008
   4.250   0.6090   0.02368   0.01412  -0.0159   0.5153   0.8022
   4.500   0.6350   0.02380   0.01426  -0.0159   0.5123   0.8036
   4.750   0.6633   0.02387   0.01434  -0.0163   0.5097   0.8052
   5.000   0.6816   0.02425   0.01490  -0.0153   0.5048   0.8073
   5.250   0.7038   0.02451   0.01526  -0.0149   0.5005   0.8097
   5.500   0.7299   0.02463   0.01544  -0.0150   0.4969   0.8121
   5.750   0.7593   0.02468   0.01550  -0.0156   0.4938   0.8143
   6.000   0.7779   0.02510   0.01609  -0.0150   0.4884   0.8168
   6.250   0.7991   0.02535   0.01647  -0.0143   0.4835   0.8186
   6.500   0.8258   0.02538   0.01657  -0.0144   0.4795   0.8204
   6.750   0.8505   0.02552   0.01679  -0.0141   0.4753   0.8224
   7.000   0.8655   0.02599   0.01746  -0.0128   0.4690   0.8250
   7.250   0.8913   0.02604   0.01760  -0.0127   0.4642   0.8277
   7.500   0.9194   0.02603   0.01764  -0.0131   0.4598   0.8306
   7.750   0.9316   0.02656   0.01838  -0.0114   0.4524   0.8339
   8.000   0.9575   0.02646   0.01837  -0.0111   0.4471   0.8363
   8.250   0.9740   0.02675   0.01883  -0.0098   0.4406   0.8392
   8.500   0.9919   0.02694   0.01916  -0.0086   0.4335   0.8424
   8.750   1.0172   0.02685   0.01917  -0.0084   0.4272   0.8455
   9.000   1.0266   0.02734   0.01985  -0.0064   0.4187   0.8494
   9.250   1.0488   0.02720   0.01981  -0.0055   0.4117   0.8524
   9.500   1.0517   0.02773   0.02055  -0.0024   0.4025   0.8570
   9.750   1.0620   0.02794   0.02087  -0.0002   0.3941   0.8620
  10.000   1.0683   0.02833   0.02141   0.0024   0.3848   0.8675
  10.250   1.0653   0.02925   0.02251   0.0057   0.3747   0.8742
  10.500   1.0727   0.02982   0.02319   0.0075   0.3642   0.8811
  10.750   1.0760   0.03058   0.02406   0.0097   0.3528   0.8885
  11.000   1.0693   0.03228   0.02591   0.0117   0.3402   0.8984
  11.250   1.0662   0.03395   0.02772   0.0132   0.3269   0.9108
  11.750   1.0735   0.03723   0.03117   0.0134   0.2958   0.9877
  12.000   1.0763   0.03919   0.03307   0.0134   0.2793   1.0000
  12.250   1.0782   0.04133   0.03516   0.0134   0.2630   1.0000
  12.750   1.0765   0.04632   0.04003   0.0132   0.2319   1.0000
  13.250   1.0707   0.05197   0.04563   0.0127   0.2032   1.0000
  13.500   1.0679   0.05493   0.04856   0.0123   0.1900   1.0000
  13.750   1.0655   0.05794   0.05157   0.0119   0.1774   1.0000
  14.000   1.0635   0.06098   0.05460   0.0113   0.1655   1.0000
  14.250   1.0618   0.06406   0.05767   0.0107   0.1545   1.0000
  14.500   1.0598   0.06723   0.06078   0.0100   0.1441   1.0000
  14.750   1.0580   0.07054   0.06415   0.0091   0.1338   1.0000
  15.000   1.0569   0.07382   0.06745   0.0083   0.1244   1.0000
  15.250   1.0548   0.07724   0.07085   0.0073   0.1160   1.0000
  15.500   1.0533   0.08076   0.07444   0.0062   0.1075   1.0000
  15.750   1.0524   0.08420   0.07791   0.0051   0.1001   1.0000
  16.000   1.0498   0.08795   0.08166   0.0037   0.0932   1.0000
  16.250   1.0490   0.09154   0.08533   0.0025   0.0865   1.0000
  16.500   1.0465   0.09538   0.08917   0.0010   0.0809   1.0000
  16.750   1.0460   0.09904   0.09292  -0.0004   0.0752   1.0000
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