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E471 (6.25%) (e471-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: E471 (6.25%) (e471-il)
Reynolds number: 1,000,000
Max Cl/Cd: 152.02 at α=1.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e471-il-1000000-n5.txt
Download as CSV file: xf-e471-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E471  (6.25%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3006   0.10779   0.10608  -0.0477   0.9928   0.0032
  -9.500  -0.2924   0.10387   0.10217  -0.0500   0.9915   0.0030
  -9.250  -0.2834   0.09989   0.09820  -0.0525   0.9900   0.0029
  -9.000  -0.2726   0.09635   0.09465  -0.0552   0.9885   0.0031
  -8.750  -0.2618   0.09238   0.09069  -0.0584   0.9870   0.0030
  -8.500  -0.2489   0.08884   0.08715  -0.0617   0.9856   0.0034
  -8.250  -0.2358   0.08480   0.08312  -0.0656   0.9843   0.0031
  -8.000  -0.2208   0.08080   0.07912  -0.0700   0.9831   0.0036
  -7.750  -0.2143   0.07698   0.07531  -0.0724   0.9789   0.0040
  -7.250  -0.1252   0.04988   0.04829  -0.0839   0.9641   0.0055
  -6.750  -0.1490   0.05743   0.05575  -0.0979   0.9608   0.0054
  -6.500  -0.1174   0.05247   0.05076  -0.1076   0.9582   0.0056
  -6.250  -0.0874   0.04798   0.04623  -0.1160   0.9534   0.0058
  -6.000  -0.0542   0.04300   0.04118  -0.1251   0.9477   0.0063
  -5.750  -0.0086   0.03516   0.03316  -0.1384   0.9440   0.0068
  -5.500   0.0298   0.02662   0.02429  -0.1478   0.9361   0.0072
  -5.250   0.0702   0.01902   0.01611  -0.1547   0.9315   0.0077
  -5.000   0.1028   0.01560   0.01225  -0.1574   0.9258   0.0080
  -4.750   0.1360   0.01304   0.00926  -0.1595   0.9205   0.0080
  -4.500   0.1676   0.01146   0.00737  -0.1607   0.9154   0.0083
  -4.250   0.1976   0.01056   0.00626  -0.1614   0.9093   0.0087
  -4.000   0.2273   0.01014   0.00572  -0.1619   0.9037   0.0092
  -3.250   0.3147   0.00802   0.00318  -0.1632   0.8846   0.0113
  -3.000   0.3436   0.00766   0.00273  -0.1635   0.8783   0.0117
  -2.750   0.3721   0.00734   0.00236  -0.1637   0.8718   0.0120
  -2.500   0.4006   0.00712   0.00207  -0.1639   0.8652   0.0127
  -2.250   0.4291   0.00687   0.00174  -0.1641   0.8577   0.0128
  -2.000   0.4575   0.00668   0.00147  -0.1641   0.8495   0.0125
  -1.750   0.4856   0.00654   0.00125  -0.1641   0.8402   0.0124
  -1.500   0.5135   0.00644   0.00108  -0.1641   0.8307   0.0123
  -1.250   0.5412   0.00637   0.00094  -0.1640   0.8208   0.0123
  -0.750   0.5962   0.00631   0.00076  -0.1638   0.7993   0.0126
  -0.500   0.6234   0.00631   0.00070  -0.1636   0.7874   0.0134
  -0.250   0.6506   0.00631   0.00066  -0.1634   0.7751   0.0167
   0.000   0.6784   0.00616   0.00066  -0.1635   0.7618   0.0993
   0.250   0.7057   0.00607   0.00070  -0.1635   0.7463   0.1758
   0.500   0.7330   0.00591   0.00078  -0.1636   0.7286   0.3026
   0.750   0.7609   0.00563   0.00093  -0.1640   0.7092   0.5095
   1.000   0.7878   0.00549   0.00107  -0.1640   0.6881   0.6624
   1.250   0.8134   0.00548   0.00119  -0.1635   0.6623   0.7587
   1.500   0.8361   0.00550   0.00133  -0.1624   0.6308   0.8604
   2.000   0.8778   0.00594   0.00157  -0.1593   0.5431   1.0000
   2.250   0.9012   0.00638   0.00176  -0.1585   0.4888   1.0000
   2.500   0.9248   0.00682   0.00196  -0.1577   0.4374   1.0000
   2.750   0.9485   0.00728   0.00218  -0.1570   0.3868   1.0000
   3.000   0.9709   0.00787   0.00246  -0.1562   0.3205   1.0000
   3.250   0.9892   0.00893   0.00294  -0.1547   0.2012   1.0000
   3.500   1.0115   0.00957   0.00327  -0.1538   0.1408   1.0000
   3.750   1.0350   0.01008   0.00358  -0.1531   0.1008   1.0000
   4.000   1.0573   0.01073   0.00397  -0.1522   0.0524   1.0000
   4.250   1.0801   0.01132   0.00437  -0.1514   0.0184   1.0000
   4.500   1.1041   0.01179   0.00475  -0.1507   0.0061   1.0000
   4.750   1.1292   0.01209   0.00509  -0.1502   0.0045   1.0000
   5.000   1.1540   0.01243   0.00550  -0.1496   0.0036   1.0000
   5.250   1.1784   0.01283   0.00598  -0.1489   0.0033   1.0000
   5.500   1.2026   0.01323   0.00642  -0.1483   0.0032   1.0000
   5.750   1.2267   0.01363   0.00685  -0.1476   0.0030   1.0000
   6.000   1.2505   0.01404   0.00731  -0.1470   0.0027   1.0000
   6.250   1.2737   0.01455   0.00787  -0.1461   0.0025   1.0000
   6.500   1.2964   0.01511   0.00853  -0.1452   0.0024   1.0000
   6.750   1.3188   0.01570   0.00918  -0.1443   0.0022   1.0000
   7.000   1.3407   0.01632   0.00987  -0.1433   0.0020   1.0000
   7.250   1.3624   0.01697   0.01058  -0.1422   0.0019   1.0000
   7.500   1.3835   0.01766   0.01134  -0.1411   0.0018   1.0000
   7.750   1.4033   0.01851   0.01227  -0.1398   0.0016   1.0000
   8.000   1.4149   0.02058   0.01455  -0.1370   0.0014   1.0000
   8.500   1.4509   0.02280   0.01700  -0.1338   0.0013   1.0000
   8.750   1.4680   0.02403   0.01840  -0.1321   0.0013   1.0000
   9.000   1.4840   0.02542   0.01994  -0.1302   0.0012   1.0000
   9.250   1.4985   0.02703   0.02172  -0.1282   0.0012   1.0000
   9.500   1.5115   0.02880   0.02368  -0.1259   0.0012   1.0000
   9.750   1.5221   0.03083   0.02594  -0.1234   0.0012   1.0000
  10.000   1.5284   0.03295   0.02828  -0.1201   0.0012   1.0000
  10.250   1.5305   0.03519   0.03075  -0.1164   0.0012   1.0000
  10.500   1.5295   0.03763   0.03342  -0.1124   0.0012   1.0000
  10.750   1.5254   0.04033   0.03637  -0.1083   0.0011   1.0000
  11.000   1.5185   0.04332   0.03961  -0.1043   0.0011   1.0000
  11.250   1.5081   0.04673   0.04326  -0.1005   0.0011   1.0000
  11.500   1.4959   0.05042   0.04718  -0.0973   0.0011   1.0000
  11.750   1.4822   0.05444   0.05143  -0.0946   0.0011   1.0000
  12.000   1.4667   0.05892   0.05612  -0.0927   0.0012   1.0000
  12.250   1.4479   0.06420   0.06163  -0.0917   0.0012   1.0000
  12.500   1.4287   0.07000   0.06762  -0.0917   0.0012   1.0000
  12.750   1.4090   0.07647   0.07428  -0.0930   0.0012   1.0000
  13.000   1.3861   0.08429   0.08230  -0.0959   0.0012   1.0000
  13.250   1.3663   0.09257   0.09074  -0.1000   0.0012   1.0000
  13.500   1.3455   0.10239   0.10072  -0.1060   0.0012   1.0000
  13.750   1.3249   0.11371   0.11220  -0.1134   0.0012   1.0000
  14.000   1.3040   0.12683   0.12545  -0.1220   0.0012   1.0000
  14.250   1.2813   0.14175   0.14050  -0.1311   0.0012   1.0000
  14.500   1.2579   0.15702   0.15585  -0.1395   0.0012   1.0000
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