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EPPLER 58 AIRFOIL (e58-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 58 AIRFOIL (e58-il)
Reynolds number: 100,000
Max Cl/Cd: 70.76 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e58-il-100000.txt
Download as CSV file: xf-e58-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 58 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.500  -0.3957   0.10947   0.10512  -0.0113   1.0000   0.0513
  -6.250  -0.4001   0.10758   0.10328  -0.0096   1.0000   0.0528
  -6.000  -0.4024   0.10561   0.10132  -0.0088   1.0000   0.0538
  -5.750  -0.4024   0.10337   0.09912  -0.0088   1.0000   0.0555
  -5.500  -0.4006   0.10115   0.09694  -0.0103   1.0000   0.0578
  -5.250  -0.3914   0.09934   0.09516  -0.0169   1.0000   0.0595
  -5.000  -0.3606   0.09656   0.09239  -0.0323   1.0000   0.0603
  -4.750  -0.3728   0.09180   0.08768  -0.0221   1.0000   0.0615
  -4.500  -0.3712   0.08880   0.08471  -0.0180   1.0000   0.0636
  -4.250  -0.3602   0.08596   0.08188  -0.0193   1.0000   0.0684
  -4.000  -0.3106   0.08101   0.07685  -0.0383   1.0000   0.0744
  -3.750  -0.3164   0.07827   0.07418  -0.0311   1.0000   0.0767
  -3.500  -0.2453   0.07306   0.06876  -0.0533   1.0000   0.0875
  -3.250  -0.2504   0.07003   0.06583  -0.0468   1.0000   0.0891
  -3.000  -0.1889   0.06525   0.06082  -0.0623   1.0000   0.1013
  -2.750  -0.1879   0.06256   0.05822  -0.0575   1.0000   0.1040
  -2.500  -0.0892   0.05820   0.05333  -0.0817   1.0000   0.1281
  -2.250  -0.0889   0.05454   0.04991  -0.0770   1.0000   0.1302
  -2.000  -0.0264   0.05164   0.04668  -0.0888   1.0000   0.1556
  -1.750  -0.0064   0.04814   0.04328  -0.0890   1.0000   0.1600
  -1.500   0.1378   0.03859   0.03237  -0.1178   1.0000   0.1148
  -1.250   0.1572   0.03781   0.03181  -0.1176   1.0000   0.1334
  -1.000   0.2840   0.02968   0.02152  -0.1369   1.0000   0.0889
  -0.750   0.3173   0.02913   0.02079  -0.1384   1.0000   0.0958
  -0.500   0.3531   0.02845   0.01970  -0.1400   1.0000   0.1007
  -0.250   0.3827   0.02831   0.01958  -0.1409   1.0000   0.1116
   0.000   0.4114   0.02836   0.01960  -0.1415   1.0000   0.1284
   0.250   0.4479   0.02808   0.01956  -0.1435   1.0000   0.1888
   0.500   0.4771   0.02828   0.01993  -0.1446   1.0000   0.2758
   0.750   0.5021   0.02872   0.02055  -0.1450   1.0000   0.3413
   1.000   0.5395   0.02830   0.02132  -0.1471   0.9985   0.6982
   1.250   0.5782   0.02880   0.02175  -0.1496   0.9855   1.0000
   1.500   0.6190   0.02956   0.02231  -0.1528   0.9743   1.0000
   1.750   0.6584   0.03021   0.02283  -0.1555   0.9629   1.0000
   2.000   0.6982   0.03074   0.02327  -0.1582   0.9514   1.0000
   2.250   0.7385   0.03114   0.02363  -0.1609   0.9399   1.0000
   2.500   0.7805   0.03137   0.02385  -0.1636   0.9284   1.0000
   2.750   0.8256   0.03136   0.02385  -0.1666   0.9169   1.0000
   3.000   0.8730   0.03110   0.02363  -0.1699   0.9061   1.0000
   3.250   0.9140   0.03075   0.02339  -0.1718   0.8934   1.0000
   3.500   0.9528   0.03036   0.02310  -0.1734   0.8809   1.0000
   3.750   0.9902   0.02995   0.02281  -0.1746   0.8687   1.0000
   4.000   1.0267   0.02950   0.02252  -0.1756   0.8567   1.0000
   4.250   1.0654   0.02877   0.02202  -0.1766   0.8441   1.0000
   4.500   1.1061   0.02768   0.02114  -0.1776   0.8305   1.0000
   4.750   1.1489   0.02611   0.01982  -0.1784   0.8154   1.0000
   5.000   1.1933   0.02399   0.01802  -0.1788   0.7988   1.0000
   5.250   1.2223   0.02274   0.01702  -0.1770   0.7732   1.0000
   5.500   1.2581   0.02115   0.01564  -0.1759   0.7329   1.0000
   5.750   1.3486   0.01906   0.01242  -0.1827   0.5053   1.0000
   6.000   1.3563   0.02075   0.01335  -0.1786   0.3917   1.0000
   6.250   1.3551   0.02293   0.01464  -0.1734   0.2584   1.0000
   6.500   1.3475   0.02718   0.01722  -0.1677   0.0808   1.0000
   6.750   1.3527   0.02975   0.01971  -0.1636   0.0630   1.0000
   7.000   1.3638   0.03182   0.02189  -0.1603   0.0558   1.0000
   7.250   1.3800   0.03429   0.02429  -0.1583   0.0502   1.0000
   7.500   1.4072   0.03646   0.02660  -0.1578   0.0446   1.0000
   7.750   1.4473   0.03937   0.02968  -0.1594   0.0414   1.0000
   8.000   1.4898   0.04310   0.03359  -0.1612   0.0399   1.0000
   8.250   1.5246   0.04724   0.03815  -0.1615   0.0399   1.0000
   8.500   1.5474   0.05131   0.04268  -0.1600   0.0397   1.0000
   8.750   1.5634   0.05626   0.04797  -0.1585   0.0385   1.0000
   9.000   1.5732   0.06091   0.05310  -0.1556   0.0383   1.0000
   9.250   1.5720   0.06393   0.05693  -0.1499   0.0401   1.0000
   9.500   1.5585   0.06988   0.06373  -0.1435   0.0436   1.0000
   9.750   1.5508   0.07557   0.06983  -0.1393   0.0460   1.0000
  10.000   1.5416   0.08102   0.07579  -0.1344   0.0520   1.0000
  10.250   1.5036   0.08619   0.08148  -0.1273   0.0553   1.0000
  10.500   1.4826   0.09187   0.08741  -0.1237   0.0583   1.0000
  10.750   1.3475   0.09100   0.08679  -0.1066   0.0467   1.0000
  11.000   1.3104   0.09607   0.09212  -0.1039   0.0469   1.0000
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