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Davis AIRFOIL (davis-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: Davis AIRFOIL (davis-il)
Reynolds number: 200,000
Max Cl/Cd: 76.05 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-davis-il-200000.txt
Download as CSV file: xf-davis-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3779   0.10261   0.09919  -0.0413   1.0000   0.0583
  -9.500  -0.3992   0.09932   0.09601  -0.0442   1.0000   0.0591
  -9.250  -0.4142   0.09614   0.09291  -0.0450   1.0000   0.0593
  -9.000  -0.4102   0.09204   0.08884  -0.0415   1.0000   0.0607
  -8.750  -0.4037   0.09053   0.08733  -0.0384   1.0000   0.0620
  -8.500  -0.4080   0.08857   0.08542  -0.0366   1.0000   0.0630
  -8.250  -0.4157   0.08672   0.08362  -0.0347   1.0000   0.0648
  -8.000  -0.4316   0.08464   0.08162  -0.0328   1.0000   0.0656
  -7.750  -0.4548   0.08295   0.08002  -0.0301   1.0000   0.0667
  -7.500  -0.4746   0.08041   0.07756  -0.0297   0.9992   0.0674
  -7.250  -0.4616   0.06562   0.06259  -0.0538   0.9872   0.0734
  -7.000  -0.4805   0.03857   0.03372  -0.0665   0.9740   0.0381
  -6.750  -0.4547   0.03391   0.02850  -0.0688   0.9696   0.0383
  -6.500  -0.4328   0.03038   0.02448  -0.0691   0.9622   0.0384
  -6.250  -0.4005   0.02733   0.02092  -0.0708   0.9585   0.0384
  -6.000  -0.3727   0.02469   0.01793  -0.0713   0.9529   0.0393
  -5.750  -0.3413   0.02309   0.01616  -0.0724   0.9473   0.0417
  -5.500  -0.3034   0.02176   0.01462  -0.0745   0.9441   0.0450
  -5.250  -0.2732   0.02059   0.01323  -0.0748   0.9385   0.0470
  -5.000  -0.2436   0.01910   0.01165  -0.0752   0.9333   0.0502
  -4.750  -0.2075   0.01823   0.01076  -0.0769   0.9302   0.0560
  -4.500  -0.1693   0.01720   0.00967  -0.0790   0.9281   0.0621
  -4.250  -0.1472   0.01671   0.00916  -0.0779   0.9193   0.0705
  -4.000  -0.1109   0.01581   0.00835  -0.0795   0.9161   0.0899
  -3.750  -0.0717   0.01497   0.00786  -0.0819   0.9141   0.1743
  -3.500  -0.0483   0.01482   0.00775  -0.0811   0.9058   0.2048
  -3.250  -0.0101   0.01456   0.00748  -0.0832   0.9026   0.2346
  -3.000   0.0297   0.01419   0.00713  -0.0855   0.9002   0.2635
  -2.750   0.0554   0.01393   0.00692  -0.0850   0.8925   0.2899
  -2.500   0.0909   0.01345   0.00657  -0.0865   0.8878   0.3288
  -2.250   0.1304   0.01290   0.00617  -0.0886   0.8846   0.3789
  -2.000   0.1529   0.01260   0.00601  -0.0873   0.8748   0.4243
  -1.750   0.1879   0.01203   0.00564  -0.0885   0.8706   0.4872
  -1.500   0.2089   0.01161   0.00550  -0.0869   0.8613   0.5575
  -1.250   0.2361   0.01070   0.00532  -0.0859   0.8561   0.7416
  -1.000   0.3219   0.01032   0.00523  -0.0967   0.8534   0.9437
  -0.750   0.3863   0.01025   0.00504  -0.1040   0.8465   0.9830
  -0.500   0.4526   0.01002   0.00466  -0.1119   0.8408   1.0000
  -0.250   0.4745   0.00996   0.00450  -0.1105   0.8284   1.0000
   0.000   0.4976   0.00992   0.00435  -0.1094   0.8158   1.0000
   0.250   0.5214   0.00988   0.00422  -0.1084   0.8032   1.0000
   0.500   0.5456   0.00987   0.00411  -0.1075   0.7905   1.0000
   0.750   0.5701   0.00989   0.00403  -0.1067   0.7782   1.0000
   1.000   0.5946   0.00994   0.00397  -0.1058   0.7657   1.0000
   1.250   0.6192   0.01001   0.00394  -0.1050   0.7530   1.0000
   1.500   0.6420   0.01011   0.00396  -0.1038   0.7396   1.0000
   1.750   0.6644   0.01023   0.00402  -0.1026   0.7260   1.0000
   2.000   0.6866   0.01035   0.00409  -0.1013   0.7124   1.0000
   2.250   0.7088   0.01048   0.00417  -0.1000   0.6988   1.0000
   2.500   0.7310   0.01061   0.00425  -0.0988   0.6853   1.0000
   2.750   0.7530   0.01073   0.00435  -0.0975   0.6716   1.0000
   3.000   0.7746   0.01085   0.00444  -0.0961   0.6571   1.0000
   3.250   0.7959   0.01096   0.00452  -0.0946   0.6418   1.0000
   3.500   0.8171   0.01108   0.00460  -0.0931   0.6255   1.0000
   3.750   0.8381   0.01121   0.00470  -0.0916   0.6086   1.0000
   4.000   0.8592   0.01137   0.00479  -0.0901   0.5913   1.0000
   4.250   0.8795   0.01157   0.00494  -0.0885   0.5721   1.0000
   4.500   0.8997   0.01183   0.00513  -0.0869   0.5522   1.0000
   4.750   0.9200   0.01217   0.00535  -0.0853   0.5322   1.0000
   5.000   0.9393   0.01251   0.00564  -0.0836   0.5102   1.0000
   5.250   0.9588   0.01288   0.00593  -0.0819   0.4894   1.0000
   5.500   0.9783   0.01323   0.00626  -0.0803   0.4695   1.0000
   5.750   0.9979   0.01357   0.00658  -0.0787   0.4511   1.0000
   6.000   1.0169   0.01389   0.00687  -0.0770   0.4329   1.0000
   6.250   1.0344   0.01422   0.00713  -0.0750   0.4139   1.0000
   6.750   1.0680   0.01495   0.00777  -0.0709   0.3749   1.0000
   7.000   1.0854   0.01539   0.00817  -0.0691   0.3592   1.0000
   7.250   1.1018   0.01587   0.00860  -0.0671   0.3426   1.0000
   7.500   1.1171   0.01633   0.00904  -0.0649   0.3245   1.0000
   7.750   1.1316   0.01674   0.00950  -0.0625   0.3050   1.0000
   8.000   1.1445   0.01717   0.00994  -0.0599   0.2847   1.0000
   8.250   1.1526   0.01761   0.01035  -0.0564   0.2520   1.0000
   8.500   1.1422   0.01911   0.01119  -0.0504   0.1405   1.0000
   8.750   1.1267   0.02160   0.01302  -0.0442   0.0612   1.0000
   9.000   1.1269   0.02316   0.01447  -0.0403   0.0447   1.0000
   9.250   1.1337   0.02429   0.01571  -0.0374   0.0396   1.0000
   9.500   1.1357   0.02572   0.01720  -0.0342   0.0366   1.0000
   9.750   1.1364   0.02727   0.01887  -0.0310   0.0346   1.0000
  10.000   1.1416   0.02862   0.02033  -0.0285   0.0326   1.0000
  10.250   1.1451   0.03015   0.02194  -0.0262   0.0307   1.0000
  10.500   1.1464   0.03194   0.02381  -0.0238   0.0296   1.0000
  10.750   1.1477   0.03385   0.02577  -0.0216   0.0289   1.0000
  11.000   1.1470   0.03611   0.02808  -0.0194   0.0280   1.0000
  11.250   1.1503   0.03841   0.03041  -0.0173   0.0272   1.0000
  11.500   1.1609   0.04006   0.03216  -0.0158   0.0268   1.0000
  11.750   1.1738   0.04173   0.03393  -0.0145   0.0263   1.0000
  12.000   1.1866   0.04343   0.03577  -0.0132   0.0255   1.0000
  12.250   1.1980   0.04518   0.03765  -0.0121   0.0245   1.0000
  12.500   1.2109   0.04707   0.03966  -0.0110   0.0238   1.0000
  12.750   1.2246   0.04917   0.04190  -0.0100   0.0233   1.0000
  13.000   1.2378   0.05162   0.04455  -0.0089   0.0232   1.0000
  13.250   1.2465   0.05443   0.04760  -0.0077   0.0231   1.0000
  13.500   1.2491   0.05780   0.05126  -0.0065   0.0234   1.0000
  13.750   1.2452   0.06169   0.05548  -0.0053   0.0239   1.0000
  14.000   1.2364   0.06591   0.06000  -0.0045   0.0243   1.0000
  14.250   1.2236   0.07058   0.06495  -0.0040   0.0248   1.0000
  14.500   1.2100   0.07533   0.06995  -0.0040   0.0252   1.0000
  14.750   1.1943   0.08049   0.07533  -0.0045   0.0257   1.0000
  15.000   1.1769   0.08597   0.08102  -0.0057   0.0260   1.0000
  15.250   1.1588   0.09187   0.08711  -0.0074   0.0264   1.0000
  15.500   1.1393   0.09819   0.09361  -0.0097   0.0266   1.0000
  15.750   0.9584   0.10320   0.09929  -0.0138   0.0260   1.0000
  16.000   0.9334   0.10974   0.10602  -0.0180   0.0263   1.0000
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