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Dormoy (dormoy-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: Dormoy (dormoy-il)
Reynolds number: 1,000,000
Max Cl/Cd: 75.18 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dormoy-il-1000000-n5.txt
Download as CSV file: xf-dormoy-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3812   0.09406   0.09253  -0.0263   1.0000   0.0024
 -10.000  -0.3785   0.09089   0.08938  -0.0273   1.0000   0.0024
  -9.750  -0.3780   0.08727   0.08579  -0.0285   1.0000   0.0024
  -9.500  -0.3741   0.08360   0.08213  -0.0304   0.9928   0.0024
  -9.250  -0.3575   0.07825   0.07678  -0.0373   0.9722   0.0024
  -9.000  -0.2938   0.06764   0.06602  -0.0617   0.9202   0.0024
  -8.750  -0.2880   0.06307   0.06111  -0.0672   0.8439   0.0024
  -6.750  -0.2119   0.03017   0.02684  -0.0747   0.7554   0.0021
  -6.500  -0.1950   0.02691   0.02326  -0.0736   0.7468   0.0020
  -6.250  -0.1758   0.02397   0.02001  -0.0723   0.7373   0.0019
  -6.000  -0.1551   0.02116   0.01685  -0.0707   0.7275   0.0020
  -5.750  -0.1325   0.01870   0.01402  -0.0690   0.7162   0.0021
  -5.500  -0.1086   0.01660   0.01157  -0.0675   0.7035   0.0024
  -5.250  -0.0856   0.01516   0.00985  -0.0666   0.6864   0.0027
  -5.000  -0.0609   0.01486   0.00939  -0.0662   0.6652   0.0037
  -4.750  -0.0361   0.01356   0.00781  -0.0652   0.6471   0.0036
  -4.500  -0.0111   0.01235   0.00638  -0.0642   0.6268   0.0033
  -4.250   0.0135   0.01127   0.00508  -0.0632   0.6005   0.0032
  -4.000   0.0368   0.01045   0.00402  -0.0619   0.5618   0.0031
  -3.750   0.0584   0.00999   0.00321  -0.0606   0.4926   0.0031
  -3.500   0.0784   0.01002   0.00271  -0.0591   0.3715   0.0033
  -3.250   0.1023   0.00989   0.00231  -0.0583   0.3253   0.0040
  -3.000   0.1276   0.00967   0.00196  -0.0578   0.3071   0.0049
  -2.750   0.1539   0.00963   0.00185  -0.0576   0.2932   0.0063
  -2.500   0.1798   0.00959   0.00166  -0.0572   0.2730   0.0073
  -2.250   0.2030   0.00980   0.00149  -0.0564   0.1887   0.0113
  -2.000   0.2284   0.00993   0.00145  -0.0560   0.1587   0.0152
  -1.750   0.2532   0.00960   0.00139  -0.0556   0.1527   0.1425
  -1.500   0.2795   0.00959   0.00140  -0.0554   0.1469   0.1688
  -1.250   0.3060   0.00957   0.00141  -0.0553   0.1417   0.1891
  -1.000   0.3297   0.00923   0.00142  -0.0548   0.1324   0.3389
  -0.750   0.3549   0.00916   0.00146  -0.0545   0.1199   0.4086
  -0.250   0.4043   0.00930   0.00167  -0.0537   0.0554   0.5045
   0.000   0.4289   0.00916   0.00176  -0.0532   0.0532   0.5906
   0.250   0.4532   0.00903   0.00185  -0.0527   0.0515   0.6721
   0.500   0.4760   0.00887   0.00195  -0.0518   0.0500   0.7633
   0.750   0.4961   0.00863   0.00209  -0.0500   0.0484   0.8821
   1.000   0.5424   0.00870   0.00232  -0.0543   0.0465   0.9656
   1.250   0.5851   0.00888   0.00252  -0.0579   0.0455   0.9845
   1.500   0.6218   0.00905   0.00270  -0.0602   0.0453   0.9944
   1.750   0.6547   0.00917   0.00278  -0.0616   0.0439   1.0000
   2.000   0.6791   0.00928   0.00287  -0.0611   0.0402   1.0000
   2.250   0.7031   0.00944   0.00300  -0.0606   0.0339   1.0000
   2.500   0.7254   0.00980   0.00330  -0.0596   0.0079   1.0000
   2.750   0.7489   0.01003   0.00357  -0.0589   0.0058   1.0000
   3.000   0.7719   0.01033   0.00392  -0.0581   0.0045   1.0000
   3.250   0.7954   0.01058   0.00420  -0.0574   0.0035   1.0000
   3.500   0.8176   0.01098   0.00465  -0.0565   0.0027   1.0000
   3.750   0.8398   0.01141   0.00514  -0.0555   0.0025   1.0000
   4.000   0.8608   0.01198   0.00579  -0.0543   0.0023   1.0000
   4.250   0.8805   0.01268   0.00660  -0.0528   0.0021   1.0000
   4.500   0.9008   0.01330   0.00728  -0.0516   0.0019   1.0000
   4.750   0.9228   0.01369   0.00772  -0.0509   0.0016   1.0000
   5.000   0.9387   0.01470   0.00884  -0.0489   0.0014   1.0000
   5.250   0.9563   0.01555   0.00978  -0.0472   0.0013   1.0000
   5.500   0.9712   0.01668   0.01102  -0.0451   0.0012   1.0000
   5.750   0.9843   0.01826   0.01273  -0.0424   0.0009   1.0000
   6.000   1.0004   0.01986   0.01443  -0.0404   0.0009   1.0000
   6.250   1.0186   0.02170   0.01640  -0.0388   0.0008   1.0000
   6.500   1.0380   0.02382   0.01868  -0.0374   0.0008   1.0000
   6.750   1.0575   0.02664   0.02173  -0.0358   0.0009   1.0000
   7.000   1.0743   0.02976   0.02514  -0.0339   0.0009   1.0000
   7.250   1.0882   0.03277   0.02839  -0.0317   0.0010   1.0000
   7.500   1.0980   0.03605   0.03192  -0.0292   0.0011   1.0000
   7.750   1.1044   0.03901   0.03512  -0.0266   0.0012   1.0000
   8.000   1.1039   0.04219   0.03852  -0.0234   0.0013   1.0000
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