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Dormoy (dormoy-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: Dormoy (dormoy-il)
Reynolds number: 500,000
Max Cl/Cd: 62.79 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dormoy-il-500000-n5.txt
Download as CSV file: xf-dormoy-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Dormoy                                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3740   0.08807   0.08598  -0.0302   1.0000   0.0043
  -9.500  -0.3732   0.08482   0.08276  -0.0312   1.0000   0.0043
  -9.250  -0.3745   0.08148   0.07946  -0.0321   1.0000   0.0043
  -9.000  -0.3787   0.07844   0.07647  -0.0326   1.0000   0.0043
  -8.750  -0.3786   0.07449   0.07256  -0.0358   0.9969   0.0043
  -8.500  -0.3609   0.06863   0.06667  -0.0441   0.9851   0.0043
  -8.250  -0.3369   0.06156   0.05954  -0.0536   0.9702   0.0043
  -8.000  -0.3078   0.05466   0.05249  -0.0624   0.9540   0.0043
  -7.750  -0.2796   0.04741   0.04502  -0.0701   0.9310   0.0044
  -7.500  -0.2556   0.04132   0.03862  -0.0754   0.8973   0.0045
  -7.250  -0.2390   0.03756   0.03451  -0.0765   0.8624   0.0046
  -7.000  -0.2247   0.03455   0.03122  -0.0762   0.8422   0.0048
  -6.750  -0.2083   0.03154   0.02789  -0.0755   0.8280   0.0048
  -6.500  -0.1908   0.02885   0.02486  -0.0746   0.8156   0.0051
  -6.250  -0.1715   0.02619   0.02186  -0.0735   0.8045   0.0052
  -6.000  -0.1508   0.02375   0.01906  -0.0722   0.7937   0.0054
  -5.000  -0.0556   0.01698   0.01101  -0.0677   0.7571   0.0065
  -4.750  -0.0310   0.01516   0.00890  -0.0666   0.7477   0.0057
  -4.500  -0.0052   0.01373   0.00724  -0.0656   0.7364   0.0051
  -4.250   0.0204   0.01256   0.00588  -0.0646   0.7246   0.0049
  -4.000   0.0452   0.01168   0.00487  -0.0637   0.7099   0.0049
  -3.750   0.0694   0.01099   0.00405  -0.0628   0.6921   0.0050
  -3.500   0.0936   0.01048   0.00338  -0.0619   0.6704   0.0055
  -3.000   0.1412   0.00982   0.00234  -0.0601   0.6083   0.0085
  -2.750   0.1641   0.00975   0.00196  -0.0590   0.5562   0.0099
  -2.500   0.1874   0.00987   0.00173  -0.0582   0.4974   0.0130
  -2.250   0.2112   0.00999   0.00151  -0.0573   0.4377   0.0184
  -2.000   0.2318   0.00990   0.00148  -0.0563   0.3612   0.1625
  -1.750   0.2559   0.00994   0.00146  -0.0559   0.3285   0.2040
  -1.500   0.2783   0.00953   0.00147  -0.0553   0.3082   0.3798
  -1.250   0.2990   0.00910   0.00151  -0.0542   0.2859   0.5628
  -1.000   0.3208   0.00894   0.00155  -0.0532   0.2587   0.6693
  -0.750   0.3377   0.00920   0.00173  -0.0512   0.1649   0.7724
  -0.500   0.3609   0.00906   0.00185  -0.0500   0.1541   0.8840
  -0.250   0.4126   0.00920   0.00199  -0.0554   0.1445   0.9578
   0.000   0.4511   0.00939   0.00208  -0.0580   0.1322   0.9784
   0.250   0.4858   0.00981   0.00224  -0.0600   0.0685   0.9902
   0.500   0.5211   0.01002   0.00239  -0.0619   0.0602   1.0000
   0.750   0.5449   0.01017   0.00253  -0.0612   0.0574   1.0000
   1.000   0.5689   0.01032   0.00267  -0.0606   0.0565   1.0000
   1.250   0.5928   0.01047   0.00283  -0.0600   0.0555   1.0000
   1.500   0.6168   0.01063   0.00302  -0.0593   0.0548   1.0000
   1.750   0.6407   0.01080   0.00321  -0.0587   0.0540   1.0000
   2.000   0.6646   0.01100   0.00343  -0.0581   0.0520   1.0000
   2.250   0.6876   0.01128   0.00374  -0.0573   0.0457   1.0000
   2.500   0.7123   0.01139   0.00379  -0.0570   0.0369   1.0000
   2.750   0.7353   0.01171   0.00407  -0.0562   0.0113   1.0000
   3.000   0.7579   0.01212   0.00461  -0.0552   0.0076   1.0000
   3.250   0.7810   0.01248   0.00506  -0.0544   0.0065   1.0000
   3.500   0.8029   0.01295   0.00561  -0.0535   0.0049   1.0000
   3.750   0.8244   0.01350   0.00625  -0.0524   0.0043   1.0000
   4.000   0.8449   0.01416   0.00700  -0.0511   0.0039   1.0000
   4.250   0.8639   0.01496   0.00789  -0.0496   0.0036   1.0000
   4.500   0.8816   0.01586   0.00888  -0.0479   0.0035   1.0000
   4.750   0.8976   0.01690   0.01005  -0.0460   0.0034   1.0000
   5.000   0.9131   0.01801   0.01126  -0.0439   0.0034   1.0000
   5.250   0.9267   0.01929   0.01255  -0.0421   0.0028   1.0000
   5.500   0.9456   0.02015   0.01355  -0.0406   0.0025   1.0000
   5.750   0.9627   0.02152   0.01506  -0.0387   0.0020   1.0000
   6.000   0.9806   0.02309   0.01674  -0.0372   0.0020   1.0000
   6.250   1.0000   0.02497   0.01877  -0.0358   0.0019   1.0000
   6.500   1.0199   0.02708   0.02105  -0.0346   0.0018   1.0000
   6.750   1.0397   0.02970   0.02391  -0.0332   0.0020   1.0000
   7.000   1.0566   0.03262   0.02710  -0.0314   0.0020   1.0000
   7.250   1.0699   0.03553   0.03031  -0.0294   0.0022   1.0000
   7.500   1.0779   0.03866   0.03370  -0.0270   0.0024   1.0000
   7.750   1.0807   0.04167   0.03693  -0.0245   0.0026   1.0000
  13.250   0.6890   0.14842   0.14654  -0.0494   0.0047   1.0000
  13.500   0.6884   0.15372   0.15185  -0.0518   0.0046   1.0000
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