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Dormoy (dormoy-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: Dormoy (dormoy-il)
Reynolds number: 50,000
Max Cl/Cd: 36.21 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dormoy-il-50000-n5.txt
Download as CSV file: xf-dormoy-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4139   0.10202   0.09595  -0.0276   1.0000   0.1509
  -9.250  -0.3935   0.09655   0.09048  -0.0254   1.0000   0.1551
  -8.750  -0.4199   0.09281   0.08707  -0.0290   1.0000   0.1660
  -8.500  -0.4032   0.08818   0.08245  -0.0258   1.0000   0.1693
  -7.500  -0.4010   0.06891   0.06324  -0.0388   1.0000   0.0764
  -7.250  -0.3966   0.06437   0.05860  -0.0399   1.0000   0.0629
  -7.000  -0.3914   0.05985   0.05375  -0.0413   1.0000   0.0535
  -6.750  -0.3864   0.05670   0.05063  -0.0397   1.0000   0.0508
  -6.500  -0.3802   0.05321   0.04699  -0.0389   1.0000   0.0476
  -6.250  -0.3670   0.04995   0.04286  -0.0387   1.0000   0.0421
  -6.000  -0.3577   0.04639   0.03937  -0.0374   1.0000   0.0405
  -5.750  -0.3455   0.04342   0.03615  -0.0364   1.0000   0.0388
  -5.500  -0.3303   0.04049   0.03278  -0.0354   1.0000   0.0369
  -5.250  -0.3122   0.03776   0.02952  -0.0344   1.0000   0.0350
  -5.000  -0.2771   0.03542   0.02623  -0.0353   0.9948   0.0328
  -4.750  -0.2426   0.03269   0.02310  -0.0369   0.9887   0.0322
  -4.500  -0.2076   0.03045   0.02043  -0.0382   0.9822   0.0317
  -4.250  -0.1715   0.02885   0.01834  -0.0393   0.9757   0.0327
  -4.000  -0.1375   0.02696   0.01628  -0.0405   0.9695   0.0352
  -3.750  -0.1036   0.02570   0.01478  -0.0413   0.9624   0.0370
  -3.500  -0.0662   0.02470   0.01345  -0.0429   0.9559   0.0388
  -3.250  -0.0332   0.02390   0.01236  -0.0438   0.9474   0.0431
  -2.750   0.0382   0.02183   0.01062  -0.0471   0.9320   0.1931
  -2.500   0.0991   0.01915   0.01036  -0.0523   0.9298   1.0000
  -2.250   0.1366   0.01924   0.00991  -0.0542   0.9179   1.0000
  -2.000   0.1759   0.01928   0.00954  -0.0564   0.9055   1.0000
  -1.750   0.2169   0.01926   0.00917  -0.0588   0.8925   1.0000
  -1.500   0.2567   0.01918   0.00877  -0.0609   0.8783   1.0000
  -1.250   0.2939   0.01912   0.00849  -0.0623   0.8642   1.0000
  -1.000   0.3282   0.01910   0.00831  -0.0633   0.8507   1.0000
  -0.750   0.3599   0.01916   0.00821  -0.0639   0.8382   1.0000
  -0.500   0.3905   0.01923   0.00819  -0.0643   0.8257   1.0000
  -0.250   0.4202   0.01929   0.00818  -0.0644   0.8119   1.0000
   0.000   0.4486   0.01935   0.00820  -0.0642   0.7968   1.0000
   0.250   0.4759   0.01941   0.00823  -0.0637   0.7805   1.0000
   0.500   0.5030   0.01944   0.00824  -0.0631   0.7632   1.0000
   0.750   0.5284   0.01949   0.00832  -0.0622   0.7447   1.0000
   1.000   0.5513   0.01959   0.00844  -0.0609   0.7242   1.0000
   1.250   0.5764   0.01962   0.00850  -0.0600   0.7047   1.0000
   1.500   0.5992   0.01972   0.00866  -0.0587   0.6827   1.0000
   1.750   0.6235   0.01974   0.00877  -0.0576   0.6591   1.0000
   2.000   0.6467   0.01977   0.00882  -0.0561   0.6309   1.0000
   2.250   0.6685   0.01984   0.00887  -0.0545   0.5960   1.0000
   2.500   0.6900   0.01997   0.00892  -0.0528   0.5576   1.0000
   2.750   0.7111   0.02023   0.00919  -0.0512   0.5204   1.0000
   3.000   0.7327   0.02059   0.00955  -0.0500   0.4892   1.0000
   3.250   0.7546   0.02100   0.01004  -0.0489   0.4627   1.0000
   3.500   0.7767   0.02145   0.01060  -0.0479   0.4400   1.0000
   3.750   0.7915   0.02213   0.01103  -0.0456   0.3854   1.0000
   4.000   0.8029   0.02318   0.01162  -0.0432   0.3204   1.0000
   4.250   0.8206   0.02397   0.01246  -0.0418   0.2782   1.0000
   4.500   0.8360   0.02499   0.01332  -0.0401   0.1992   1.0000
   4.750   0.8387   0.02781   0.01506  -0.0376   0.0645   1.0000
   5.000   0.8512   0.02985   0.01729  -0.0356   0.0439   1.0000
   5.250   0.8666   0.03135   0.01907  -0.0339   0.0344   1.0000
   5.500   0.8803   0.03289   0.02094  -0.0321   0.0309   1.0000
   5.750   0.8905   0.03464   0.02291  -0.0301   0.0286   1.0000
   6.000   0.8990   0.03637   0.02489  -0.0279   0.0270   1.0000
   6.250   0.9046   0.03816   0.02688  -0.0255   0.0250   1.0000
   6.500   0.9086   0.03999   0.02888  -0.0232   0.0237   1.0000
   6.750   0.9110   0.04204   0.03108  -0.0209   0.0226   1.0000
   7.000   0.9150   0.04424   0.03342  -0.0188   0.0222   1.0000
   7.250   0.9262   0.04640   0.03571  -0.0169   0.0219   1.0000
   7.500   0.9598   0.04872   0.03813  -0.0160   0.0217   1.0000
   7.750   1.0048   0.05214   0.04178  -0.0169   0.0217   1.0000
   8.000   1.0313   0.05585   0.04590  -0.0166   0.0217   1.0000
   8.250   1.0441   0.05926   0.04966  -0.0153   0.0217   1.0000
   8.500   1.0479   0.06241   0.05316  -0.0134   0.0216   1.0000
   8.750   1.0457   0.06560   0.05668  -0.0112   0.0215   1.0000
   9.000   1.0402   0.06871   0.06009  -0.0092   0.0214   1.0000
   9.250   1.0321   0.07204   0.06369  -0.0077   0.0214   1.0000
   9.500   1.0214   0.07567   0.06757  -0.0067   0.0214   1.0000
   9.750   1.0081   0.07955   0.07168  -0.0065   0.0214   1.0000
  10.000   0.9958   0.08376   0.07609  -0.0069   0.0215   1.0000
  10.250   0.9840   0.08827   0.08077  -0.0079   0.0217   1.0000
  10.500   0.9700   0.09327   0.08594  -0.0096   0.0217   1.0000
  10.750   0.9563   0.09852   0.09134  -0.0119   0.0218   1.0000
  11.000   0.9383   0.10409   0.09719  -0.0157   0.0223   1.0000
  11.250   0.9139   0.11202   0.10531  -0.0216   0.0229   1.0000
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