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E471 (6.25%) (e471-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: E471 (6.25%) (e471-il)
Reynolds number: 500,000
Max Cl/Cd: 138.49 at α=2°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e471-il-500000-n5.txt
Download as CSV file: xf-e471-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2170   0.09648   0.09427  -0.0504   0.9881   0.0072
  -9.250  -0.2099   0.09217   0.08996  -0.0525   0.9867   0.0066
  -8.750  -0.3003   0.10026   0.09796  -0.0443   0.9917   0.0063
  -8.500  -0.2891   0.09655   0.09426  -0.0472   0.9895   0.0065
  -8.250  -0.2786   0.09184   0.08956  -0.0510   0.9871   0.0057
  -8.000  -0.2641   0.08847   0.08619  -0.0546   0.9851   0.0061
  -7.750  -0.2485   0.08482   0.08251  -0.0587   0.9833   0.0065
  -7.500  -0.2379   0.08150   0.07921  -0.0614   0.9792   0.0072
  -7.250  -0.2260   0.07804   0.07575  -0.0649   0.9742   0.0083
  -7.000  -0.2087   0.07375   0.07147  -0.0702   0.9709   0.0079
  -6.750  -0.1921   0.06952   0.06724  -0.0758   0.9645   0.0089
  -6.500  -0.1715   0.06486   0.06258  -0.0825   0.9601   0.0086
  -6.250  -0.1424   0.05921   0.05690  -0.0921   0.9575   0.0086
  -6.000  -0.1197   0.05401   0.05167  -0.0995   0.9501   0.0088
  -5.750  -0.0817   0.04745   0.04504  -0.1110   0.9467   0.0091
  -5.250   0.0063   0.03031   0.02738  -0.1364   0.9390   0.0107
  -5.000   0.0353   0.02955   0.02656  -0.1386   0.9358   0.0121
  -4.750   0.0784   0.02351   0.02006  -0.1455   0.9335   0.0124
  -4.500   0.1247   0.01664   0.01228  -0.1516   0.9320   0.0112
  -4.250   0.1587   0.01454   0.00979  -0.1536   0.9290   0.0113
  -4.000   0.1897   0.01318   0.00817  -0.1546   0.9245   0.0117
  -3.750   0.2227   0.01214   0.00692  -0.1559   0.9214   0.0125
  -3.500   0.2565   0.01127   0.00585  -0.1573   0.9188   0.0134
  -3.250   0.2870   0.01059   0.00504  -0.1580   0.9143   0.0140
  -3.000   0.3179   0.01004   0.00438  -0.1587   0.9097   0.0147
  -2.750   0.3501   0.00960   0.00387  -0.1597   0.9059   0.0157
  -2.500   0.3806   0.00909   0.00328  -0.1603   0.9009   0.0156
  -2.250   0.4113   0.00865   0.00275  -0.1609   0.8956   0.0155
  -1.750   0.4719   0.00808   0.00202  -0.1619   0.8846   0.0154
  -1.500   0.5022   0.00790   0.00176  -0.1624   0.8787   0.0154
  -1.250   0.5308   0.00778   0.00156  -0.1625   0.8711   0.0156
  -1.000   0.5602   0.00768   0.00138  -0.1627   0.8637   0.0160
  -0.750   0.5882   0.00762   0.00127  -0.1627   0.8546   0.0169
  -0.500   0.6171   0.00741   0.00120  -0.1629   0.8456   0.0755
  -0.250   0.6465   0.00706   0.00122  -0.1635   0.8363   0.2251
   0.000   0.6751   0.00676   0.00129  -0.1640   0.8260   0.3762
   0.250   0.7034   0.00616   0.00150  -0.1644   0.8150   0.6831
   0.500   0.7280   0.00596   0.00157  -0.1636   0.8035   0.8016
   0.750   0.7456   0.00570   0.00153  -0.1608   0.7915   1.0000
   1.000   0.7727   0.00580   0.00155  -0.1606   0.7776   1.0000
   1.250   0.7995   0.00591   0.00158  -0.1603   0.7618   1.0000
   1.500   0.8261   0.00603   0.00163  -0.1599   0.7450   1.0000
   1.750   0.8523   0.00617   0.00169  -0.1595   0.7264   1.0000
   2.000   0.8780   0.00634   0.00179  -0.1590   0.7039   1.0000
   2.250   0.9030   0.00656   0.00189  -0.1584   0.6762   1.0000
   2.500   0.9271   0.00683   0.00202  -0.1575   0.6411   1.0000
   2.750   0.9498   0.00720   0.00218  -0.1565   0.5960   1.0000
   3.000   0.9713   0.00768   0.00241  -0.1552   0.5407   1.0000
   3.250   0.9923   0.00825   0.00273  -0.1539   0.4799   1.0000
   3.500   1.0131   0.00889   0.00306  -0.1527   0.4156   1.0000
   3.750   1.0290   0.01007   0.00359  -0.1508   0.2937   1.0000
   4.000   1.0468   0.01116   0.00412  -0.1492   0.1899   1.0000
   4.250   1.0678   0.01193   0.00456  -0.1482   0.1305   1.0000
   4.500   1.0900   0.01256   0.00498  -0.1474   0.0902   1.0000
   4.750   1.1109   0.01335   0.00550  -0.1463   0.0439   1.0000
   5.000   1.1317   0.01417   0.00616  -0.1451   0.0107   1.0000
   5.250   1.1554   0.01463   0.00664  -0.1444   0.0069   1.0000
   5.500   1.1790   0.01509   0.00716  -0.1436   0.0059   1.0000
   5.750   1.2023   0.01560   0.00775  -0.1427   0.0053   1.0000
   6.000   1.2250   0.01616   0.00841  -0.1418   0.0049   1.0000
   6.250   1.2471   0.01681   0.00916  -0.1407   0.0046   1.0000
   6.500   1.2681   0.01759   0.01004  -0.1395   0.0043   1.0000
   6.750   1.2855   0.01886   0.01153  -0.1376   0.0035   1.0000
   7.000   1.3036   0.01999   0.01278  -0.1359   0.0033   1.0000
   7.250   1.3232   0.02089   0.01378  -0.1345   0.0032   1.0000
   7.500   1.3420   0.02190   0.01490  -0.1330   0.0030   1.0000
   7.750   1.3601   0.02304   0.01616  -0.1313   0.0029   1.0000
   8.000   1.3774   0.02433   0.01760  -0.1296   0.0027   1.0000
   8.250   1.3942   0.02579   0.01922  -0.1278   0.0026   1.0000
   8.500   1.4105   0.02743   0.02105  -0.1260   0.0024   1.0000
   8.750   1.4261   0.02927   0.02309  -0.1240   0.0024   1.0000
   9.000   1.4406   0.03131   0.02540  -0.1220   0.0023   1.0000
   9.250   1.4531   0.03362   0.02798  -0.1198   0.0022   1.0000
   9.500   1.4627   0.03609   0.03074  -0.1171   0.0022   1.0000
   9.750   1.4672   0.03875   0.03369  -0.1138   0.0022   1.0000
  10.000   1.4670   0.04153   0.03677  -0.1099   0.0022   1.0000
  10.250   1.4628   0.04453   0.04007  -0.1058   0.0022   1.0000
  10.500   1.4551   0.04779   0.04362  -0.1018   0.0022   1.0000
  10.750   1.4441   0.05141   0.04753  -0.0980   0.0022   1.0000
  11.000   1.4305   0.05539   0.05179  -0.0947   0.0022   1.0000
  11.250   1.4139   0.05989   0.05656  -0.0920   0.0022   1.0000
  11.500   1.3959   0.06482   0.06174  -0.0902   0.0022   1.0000
  11.750   1.3769   0.07024   0.06739  -0.0896   0.0022   1.0000
  12.000   1.3569   0.07628   0.07365  -0.0901   0.0023   1.0000
  12.250   1.3355   0.08322   0.08079  -0.0920   0.0023   1.0000
  12.500   1.3140   0.09104   0.08881  -0.0954   0.0023   1.0000
  12.750   1.2933   0.09988   0.09782  -0.1005   0.0023   1.0000
  13.000   1.2717   0.11062   0.10873  -0.1076   0.0023   1.0000
  13.250   1.2523   0.12284   0.12111  -0.1160   0.0023   1.0000
  13.500   1.2287   0.13916   0.13755  -0.1263   0.0024   1.0000
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