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EPPLER 472 AIRFOIL (e472-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 472 AIRFOIL (e472-il)
Reynolds number: 100,000
Max Cl/Cd: 26.55 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e472-il-100000.txt
Download as CSV file: xf-e472-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 472 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.7600   0.07873   0.07271  -0.0218   1.0000   0.1647
 -10.250  -0.7733   0.07285   0.06681  -0.0232   1.0000   0.1654
 -10.000  -0.7886   0.06800   0.06195  -0.0233   1.0000   0.1663
  -9.750  -0.8009   0.06426   0.05818  -0.0221   1.0000   0.1677
  -9.500  -0.8126   0.06048   0.05433  -0.0210   1.0000   0.1697
  -9.250  -0.8491   0.05379   0.04738  -0.0195   1.0000   0.1708
  -9.000  -0.8628   0.04945   0.04277  -0.0174   1.0000   0.1736
  -8.750  -0.8774   0.04482   0.03771  -0.0146   1.0000   0.1767
  -8.500  -0.8906   0.04063   0.03284  -0.0110   1.0000   0.1801
  -8.250  -0.8635   0.03990   0.03236  -0.0106   1.0000   0.1837
  -8.000  -0.8443   0.03898   0.03142  -0.0093   1.0000   0.1879
  -7.750  -0.8366   0.03668   0.02878  -0.0070   1.0000   0.1924
  -7.500  -0.8300   0.03425   0.02589  -0.0044   1.0000   0.1967
  -7.250  -0.8063   0.03345   0.02525  -0.0036   1.0000   0.2006
  -7.000  -0.7875   0.03240   0.02412  -0.0021   1.0000   0.2055
  -6.750  -0.7744   0.03076   0.02207   0.0000   1.0000   0.2105
  -6.500  -0.7557   0.02937   0.02061   0.0014   1.0000   0.2147
  -6.250  -0.7335   0.02863   0.01991   0.0025   1.0000   0.2196
  -6.000  -0.7150   0.02757   0.01863   0.0042   1.0000   0.2252
  -5.750  -0.6963   0.02633   0.01718   0.0057   1.0000   0.2300
  -5.500  -0.6739   0.02556   0.01648   0.0068   1.0000   0.2349
  -5.250  -0.6530   0.02478   0.01558   0.0082   1.0000   0.2410
  -5.000  -0.6326   0.02383   0.01446   0.0096   1.0000   0.2465
  -4.750  -0.6099   0.02311   0.01380   0.0106   1.0000   0.2516
  -4.500  -0.5882   0.02244   0.01303   0.0119   1.0000   0.2579
  -4.250  -0.5663   0.02168   0.01221   0.0131   1.0000   0.2640
  -4.000  -0.5437   0.02110   0.01169   0.0142   1.0000   0.2702
  -3.750  -0.5217   0.02054   0.01098   0.0155   1.0000   0.2770
  -3.500  -0.4988   0.01988   0.01044   0.0165   1.0000   0.2833
  -3.250  -0.4764   0.01941   0.00996   0.0177   1.0000   0.2911
  -3.000  -0.4539   0.01886   0.00944   0.0188   1.0000   0.2984
  -2.750  -0.4313   0.01841   0.00906   0.0199   1.0000   0.3062
  -2.500  -0.4090   0.01796   0.00864   0.0210   1.0000   0.3148
  -2.250  -0.3869   0.01758   0.00836   0.0222   1.0000   0.3243
  -2.000  -0.3650   0.01718   0.00806   0.0233   1.0000   0.3340
  -1.750  -0.3435   0.01689   0.00780   0.0245   1.0000   0.3454
  -1.500  -0.3224   0.01655   0.00767   0.0257   1.0000   0.3573
  -1.250  -0.3022   0.01628   0.00757   0.0270   1.0000   0.3713
  -1.000  -0.2830   0.01605   0.00752   0.0284   1.0000   0.3874
  -0.750  -0.2260   0.01569   0.00751   0.0224   0.9837   0.4201
  -0.500  -0.1622   0.01489   0.00724   0.0158   0.9560   0.4760
  -0.250  -0.1103   0.01376   0.00685   0.0123   0.9181   0.5714
   0.000   0.0006   0.01247   0.00676  -0.0001   0.8320   0.8332
   0.250   0.1103   0.01376   0.00685  -0.0123   0.5713   0.9181
   0.500   0.1624   0.01489   0.00724  -0.0158   0.4758   0.9560
   0.750   0.2260   0.01569   0.00751  -0.0225   0.4199   0.9837
   1.000   0.2830   0.01605   0.00752  -0.0284   0.3875   1.0000
   1.250   0.3022   0.01628   0.00756  -0.0270   0.3713   1.0000
   1.500   0.3224   0.01655   0.00767  -0.0257   0.3572   1.0000
   1.750   0.3435   0.01689   0.00780  -0.0245   0.3455   1.0000
   2.000   0.3650   0.01718   0.00806  -0.0233   0.3340   1.0000
   2.250   0.3869   0.01758   0.00836  -0.0222   0.3244   1.0000
   2.500   0.4089   0.01796   0.00864  -0.0210   0.3148   1.0000
   2.750   0.4313   0.01841   0.00906  -0.0199   0.3062   1.0000
   3.000   0.4538   0.01886   0.00944  -0.0188   0.2984   1.0000
   3.250   0.4764   0.01941   0.00996  -0.0177   0.2911   1.0000
   3.500   0.4987   0.01988   0.01043  -0.0165   0.2833   1.0000
   3.750   0.5217   0.02053   0.01097  -0.0155   0.2771   1.0000
   4.000   0.5437   0.02110   0.01169  -0.0142   0.2702   1.0000
   4.250   0.5663   0.02168   0.01221  -0.0131   0.2640   1.0000
   4.500   0.5882   0.02244   0.01303  -0.0119   0.2579   1.0000
   4.750   0.6099   0.02310   0.01380  -0.0106   0.2516   1.0000
   5.000   0.6326   0.02383   0.01446  -0.0095   0.2465   1.0000
   5.250   0.6530   0.02479   0.01559  -0.0082   0.2410   1.0000
   5.500   0.6739   0.02556   0.01648  -0.0068   0.2349   1.0000
   5.750   0.6963   0.02633   0.01718  -0.0057   0.2300   1.0000
   6.000   0.7151   0.02757   0.01863  -0.0042   0.2253   1.0000
   6.250   0.7335   0.02863   0.01991  -0.0025   0.2196   1.0000
   6.500   0.7557   0.02938   0.02061  -0.0014   0.2147   1.0000
   6.750   0.7744   0.03076   0.02207   0.0000   0.2106   1.0000
   7.000   0.7875   0.03241   0.02413   0.0021   0.2055   1.0000
   7.250   0.8063   0.03346   0.02526   0.0036   0.2007   1.0000
   7.500   0.8300   0.03425   0.02590   0.0044   0.1967   1.0000
   7.750   0.8367   0.03668   0.02877   0.0070   0.1925   1.0000
   8.000   0.8443   0.03897   0.03142   0.0092   0.1879   1.0000
   8.250   0.8634   0.03992   0.03238   0.0106   0.1837   1.0000
   8.500   0.8905   0.04062   0.03284   0.0110   0.1801   1.0000
   8.750   0.8775   0.04481   0.03770   0.0146   0.1767   1.0000
   9.000   0.8631   0.04941   0.04273   0.0174   0.1735   1.0000
   9.250   0.8487   0.05386   0.04746   0.0195   0.1709   1.0000
   9.500   0.8085   0.06093   0.05479   0.0209   0.1698   1.0000
   9.750   0.8024   0.06415   0.05806   0.0221   0.1677   1.0000
  10.000   0.7876   0.06814   0.06208   0.0232   0.1664   1.0000
  10.250   0.7731   0.07293   0.06690   0.0231   0.1654   1.0000
  10.500   0.7609   0.07866   0.07265   0.0218   0.1647   1.0000
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