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Davis AIRFOIL (davis-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: Davis AIRFOIL (davis-il)
Reynolds number: 50,000
Max Cl/Cd: 22.18 at α=11°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-davis-il-50000.txt
Download as CSV file: xf-davis-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Davis AIRFOIL                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3662   0.10925   0.10265  -0.0292   1.0000   0.2424
  -8.500  -0.3460   0.10434   0.09773  -0.0275   1.0000   0.2514
  -8.250  -0.3711   0.10416   0.09773  -0.0266   1.0000   0.2574
  -8.000  -0.3530   0.09951   0.09306  -0.0248   1.0000   0.2665
  -7.750  -0.3869   0.09992   0.09370  -0.0228   1.0000   0.2727
  -7.500  -0.3654   0.09497   0.08871  -0.0212   1.0000   0.2803
  -7.250  -0.3996   0.09525   0.08922  -0.0181   1.0000   0.2875
  -7.000  -0.3865   0.09105   0.08502  -0.0163   1.0000   0.2939
  -6.750  -0.4155   0.09074   0.08489  -0.0126   1.0000   0.3017
  -6.500  -0.4190   0.08783   0.08206  -0.0101   1.0000   0.3072
  -6.250  -0.4420   0.08685   0.08122  -0.0078   1.0000   0.3173
  -6.000  -0.4373   0.08350   0.07792  -0.0051   1.0000   0.3241
  -5.750  -0.4864   0.06760   0.06162  -0.0320   1.0000   0.1698
  -5.500  -0.4816   0.05836   0.05193  -0.0363   1.0000   0.1411
  -5.250  -0.4712   0.05418   0.04755  -0.0361   1.0000   0.1361
  -5.000  -0.4594   0.04917   0.04214  -0.0370   1.0000   0.1320
  -4.750  -0.4444   0.04504   0.03752  -0.0375   1.0000   0.1325
  -4.500  -0.4267   0.04151   0.03342  -0.0376   1.0000   0.1355
  -4.250  -0.4066   0.03817   0.02940  -0.0375   1.0000   0.1377
  -4.000  -0.3866   0.03577   0.02662  -0.0368   1.0000   0.1433
  -3.750  -0.3660   0.03407   0.02449  -0.0360   1.0000   0.1534
  -3.500  -0.3457   0.03247   0.02277  -0.0350   1.0000   0.1639
  -3.250  -0.3250   0.03117   0.02124  -0.0341   1.0000   0.1810
  -3.000  -0.3049   0.03008   0.02014  -0.0329   1.0000   0.2062
  -2.750  -0.2842   0.02896   0.01897  -0.0317   1.0000   0.2576
  -2.500  -0.2667   0.02826   0.01850  -0.0302   1.0000   0.3173
  -2.250  -0.2524   0.02819   0.01868  -0.0283   1.0000   0.3688
  -2.000  -0.2373   0.02808   0.01869  -0.0264   1.0000   0.4163
  -1.750  -0.2175   0.02778   0.01834  -0.0255   1.0000   0.4566
  -1.500  -0.1957   0.02746   0.01800  -0.0250   1.0000   0.5004
  -1.250  -0.1736   0.02703   0.01776  -0.0245   1.0000   0.5564
  -1.000  -0.1524   0.02637   0.01770  -0.0234   1.0000   0.6498
  -0.750  -0.1055   0.02553   0.01733  -0.0282   1.0000   1.0000
  -0.500  -0.0856   0.02616   0.01747  -0.0285   1.0000   1.0000
  -0.250  -0.0675   0.02682   0.01779  -0.0283   1.0000   1.0000
   0.000  -0.0226   0.02822   0.01880  -0.0332   0.9884   1.0000
   0.250   0.0213   0.02957   0.01980  -0.0377   0.9753   1.0000
   0.500   0.0698   0.03091   0.02086  -0.0428   0.9591   1.0000
   0.750   0.1190   0.03209   0.02178  -0.0477   0.9407   1.0000
   1.000   0.1597   0.03291   0.02242  -0.0510   0.9218   1.0000
   1.250   0.1990   0.03374   0.02310  -0.0538   0.9055   1.0000
   1.500   0.2351   0.03454   0.02378  -0.0561   0.8907   1.0000
   1.750   0.2703   0.03530   0.02445  -0.0581   0.8760   1.0000
   2.000   0.3052   0.03601   0.02509  -0.0600   0.8611   1.0000
   2.250   0.3405   0.03667   0.02569  -0.0617   0.8457   1.0000
   2.500   0.3768   0.03725   0.02623  -0.0635   0.8301   1.0000
   2.750   0.4140   0.03776   0.02673  -0.0652   0.8144   1.0000
   3.000   0.4539   0.03811   0.02710  -0.0671   0.7986   1.0000
   3.250   0.4955   0.03833   0.02735  -0.0690   0.7829   1.0000
   3.500   0.5161   0.03894   0.02800  -0.0680   0.7631   1.0000
   3.750   0.5504   0.03921   0.02831  -0.0687   0.7454   1.0000
   4.000   0.5890   0.03925   0.02842  -0.0697   0.7284   1.0000
   4.250   0.6292   0.03911   0.02839  -0.0706   0.7121   1.0000
   4.500   0.6689   0.03890   0.02827  -0.0714   0.6964   1.0000
   4.750   0.7084   0.03862   0.02810  -0.0720   0.6811   1.0000
   5.000   0.7450   0.03854   0.02815  -0.0724   0.6659   1.0000
   5.250   0.7779   0.03864   0.02837  -0.0724   0.6509   1.0000
   5.500   0.8053   0.03905   0.02888  -0.0719   0.6364   1.0000
   5.750   0.8271   0.03981   0.02977  -0.0709   0.6223   1.0000
   6.000   0.8446   0.04087   0.03093  -0.0696   0.6086   1.0000
   6.250   0.8567   0.04233   0.03248  -0.0679   0.5956   1.0000
   6.500   0.8616   0.04436   0.03459  -0.0657   0.5835   1.0000
   6.750   0.9294   0.04261   0.03315  -0.0688   0.5766   1.0000
   7.000   0.9114   0.04615   0.03672  -0.0649   0.5638   1.0000
   7.250   0.8732   0.05159   0.04210  -0.0606   0.5515   1.0000
   7.500   0.8474   0.05708   0.04757  -0.0589   0.5417   1.0000
   7.750   0.8704   0.05838   0.04904  -0.0585   0.5342   1.0000
   8.000   0.8277   0.06546   0.05602  -0.0571   0.5258   1.0000
   8.250   0.8410   0.06790   0.05860  -0.0569   0.5196   1.0000
   8.500   0.8266   0.07273   0.06345  -0.0565   0.5145   1.0000
   8.750   0.8071   0.07786   0.06859  -0.0563   0.5102   1.0000
   9.000   0.8452   0.07849   0.06948  -0.0562   0.5022   1.0000
   9.250   0.8147   0.08459   0.07554  -0.0563   0.4996   1.0000
   9.500   0.8010   0.08920   0.08020  -0.0564   0.4959   1.0000
   9.750   0.8153   0.09108   0.08225  -0.0556   0.4818   1.0000
  10.000   0.8621   0.08912   0.08066  -0.0530   0.4554   1.0000
  10.250   0.8692   0.09109   0.08279  -0.0518   0.4388   1.0000
  10.500   0.9235   0.08724   0.07942  -0.0480   0.4119   1.0000
  10.750   0.9336   0.08820   0.08065  -0.0459   0.3904   1.0000
  11.000   1.0928   0.04928   0.03959  -0.0164   0.1264   1.0000
  11.250   1.0965   0.05203   0.04219  -0.0145   0.1133   1.0000
  11.500   1.1274   0.05383   0.04390  -0.0127   0.1011   1.0000
  11.750   1.1839   0.05624   0.04626  -0.0127   0.0902   1.0000
  12.000   1.2009   0.05925   0.04963  -0.0117   0.0857   1.0000
  12.250   1.2256   0.06280   0.05347  -0.0113   0.0827   1.0000
  12.500   1.2411   0.06687   0.05782  -0.0105   0.0814   1.0000
  12.750   1.2410   0.07083   0.06210  -0.0091   0.0810   1.0000
  13.000   1.2307   0.07479   0.06639  -0.0074   0.0811   1.0000
  13.250   1.2116   0.07890   0.07083  -0.0061   0.0814   1.0000
  13.500   1.1765   0.08372   0.07603  -0.0056   0.0826   1.0000
  13.750   1.1410   0.08970   0.08232  -0.0068   0.0837   1.0000
  14.000   1.1033   0.09698   0.08987  -0.0097   0.0851   1.0000
  14.250   1.0637   0.10581   0.09887  -0.0144   0.0868   1.0000
  14.500   1.0271   0.11585   0.10903  -0.0203   0.0888   1.0000
  14.750   1.0012   0.12563   0.11885  -0.0257   0.0906   1.0000
  15.000   0.9870   0.13412   0.12735  -0.0297   0.0918   1.0000
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