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Davis AIRFOIL (davis-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: Davis AIRFOIL (davis-il)
Reynolds number: 100,000
Max Cl/Cd: 54.01 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-davis-il-100000.txt
Download as CSV file: xf-davis-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3617   0.10195   0.09722  -0.0362   1.0000   0.1214
  -8.750  -0.3931   0.10097   0.09640  -0.0377   1.0000   0.1248
  -8.500  -0.4276   0.10020   0.09581  -0.0376   1.0000   0.1253
  -8.250  -0.3982   0.09451   0.09008  -0.0346   1.0000   0.1278
  -8.000  -0.3930   0.09196   0.08756  -0.0321   1.0000   0.1305
  -7.750  -0.4029   0.09000   0.08568  -0.0300   1.0000   0.1337
  -7.500  -0.4249   0.08854   0.08434  -0.0276   1.0000   0.1360
  -7.000  -0.4973   0.08389   0.07989  -0.0315   1.0000   0.1404
  -6.750  -0.4882   0.08095   0.07702  -0.0265   1.0000   0.1418
  -6.500  -0.4851   0.07891   0.07502  -0.0227   1.0000   0.1444
  -6.250  -0.4900   0.07662   0.07275  -0.0215   1.0000   0.1490
  -6.000  -0.5255   0.04848   0.04330  -0.0406   1.0000   0.0731
  -5.750  -0.5151   0.04415   0.03855  -0.0401   1.0000   0.0701
  -5.500  -0.5030   0.04010   0.03403  -0.0396   1.0000   0.0698
  -5.250  -0.4882   0.03649   0.02987  -0.0388   1.0000   0.0696
  -5.000  -0.4540   0.03260   0.02525  -0.0410   0.9954   0.0692
  -4.750  -0.4189   0.03006   0.02198  -0.0427   0.9900   0.0709
  -4.500  -0.3831   0.02811   0.01983  -0.0448   0.9849   0.0762
  -4.250  -0.3483   0.02670   0.01811  -0.0462   0.9789   0.0809
  -4.000  -0.3116   0.02550   0.01676  -0.0480   0.9731   0.0890
  -3.750  -0.2769   0.02465   0.01574  -0.0493   0.9671   0.0989
  -3.500  -0.2431   0.02395   0.01516  -0.0507   0.9604   0.1165
  -3.250  -0.2076   0.02310   0.01448  -0.0523   0.9545   0.1592
  -3.000  -0.1765   0.02279   0.01440  -0.0533   0.9463   0.2357
  -2.750  -0.1416   0.02275   0.01434  -0.0550   0.9394   0.2766
  -2.500  -0.1098   0.02270   0.01436  -0.0562   0.9314   0.3160
  -2.250  -0.0778   0.02262   0.01440  -0.0573   0.9240   0.3563
  -2.000  -0.0438   0.02241   0.01431  -0.0586   0.9163   0.3997
  -1.750  -0.0130   0.02212   0.01419  -0.0593   0.9080   0.4480
  -1.500   0.0236   0.02161   0.01399  -0.0609   0.9013   0.5205
  -1.250   0.1205   0.02018   0.01393  -0.0734   0.9020   1.0000
  -1.000   0.1550   0.02026   0.01370  -0.0749   0.8920   1.0000
  -0.750   0.2059   0.02012   0.01329  -0.0791   0.8854   1.0000
  -0.500   0.2369   0.02009   0.01308  -0.0796   0.8738   1.0000
  -0.250   0.2751   0.01998   0.01281  -0.0814   0.8644   1.0000
   0.000   0.3240   0.01963   0.01231  -0.0849   0.8576   1.0000
   0.250   0.3582   0.01945   0.01202  -0.0858   0.8469   1.0000
   0.500   0.4132   0.01884   0.01131  -0.0902   0.8419   1.0000
   0.750   0.4414   0.01874   0.01114  -0.0900   0.8304   1.0000
   1.000   0.4768   0.01851   0.01085  -0.0909   0.8216   1.0000
   1.250   0.5178   0.01811   0.01040  -0.0928   0.8139   1.0000
   1.500   0.5461   0.01801   0.01026  -0.0925   0.8026   1.0000
   1.750   0.5817   0.01773   0.00994  -0.0933   0.7930   1.0000
   2.000   0.6211   0.01733   0.00950  -0.0948   0.7840   1.0000
   2.250   0.6488   0.01724   0.00940  -0.0942   0.7713   1.0000
   2.500   0.6777   0.01715   0.00929  -0.0939   0.7586   1.0000
   2.750   0.7070   0.01707   0.00919  -0.0936   0.7457   1.0000
   3.000   0.7360   0.01702   0.00912  -0.0933   0.7322   1.0000
   3.250   0.7639   0.01702   0.00910  -0.0928   0.7180   1.0000
   3.500   0.7903   0.01706   0.00912  -0.0920   0.7028   1.0000
   3.750   0.8154   0.01713   0.00920  -0.0910   0.6866   1.0000
   4.000   0.8398   0.01720   0.00926  -0.0898   0.6696   1.0000
   4.250   0.8647   0.01724   0.00929  -0.0888   0.6519   1.0000
   4.500   0.8889   0.01728   0.00931  -0.0876   0.6330   1.0000
   4.750   0.9095   0.01741   0.00946  -0.0858   0.6116   1.0000
   5.000   0.9352   0.01750   0.00947  -0.0849   0.5917   1.0000
   5.250   0.9567   0.01780   0.00974  -0.0834   0.5702   1.0000
   5.500   0.9812   0.01817   0.01004  -0.0825   0.5507   1.0000
   5.750   1.0068   0.01864   0.01044  -0.0819   0.5330   1.0000
   6.000   1.0302   0.01920   0.01097  -0.0810   0.5163   1.0000
   6.250   1.0539   0.01979   0.01157  -0.0802   0.5016   1.0000
   6.500   1.0770   0.02039   0.01226  -0.0793   0.4885   1.0000
   6.750   1.0979   0.02097   0.01295  -0.0781   0.4755   1.0000
   7.000   1.1181   0.02136   0.01340  -0.0766   0.4603   1.0000
   7.250   1.1353   0.02152   0.01355  -0.0743   0.4415   1.0000
   7.500   1.1472   0.02161   0.01372  -0.0712   0.4204   1.0000
   7.750   1.1612   0.02172   0.01380  -0.0684   0.3999   1.0000
   8.000   1.1697   0.02195   0.01408  -0.0649   0.3766   1.0000
   8.250   1.1794   0.02234   0.01442  -0.0616   0.3538   1.0000
   8.500   1.1852   0.02282   0.01491  -0.0577   0.3284   1.0000
   8.750   1.1848   0.02339   0.01548  -0.0529   0.2974   1.0000
   9.000   1.1731   0.02405   0.01616  -0.0462   0.2440   1.0000
   9.250   1.1475   0.02644   0.01761  -0.0389   0.1231   1.0000
   9.500   1.1304   0.02942   0.02011  -0.0335   0.0872   1.0000
   9.750   1.1232   0.03172   0.02237  -0.0295   0.0756   1.0000
  10.000   1.1178   0.03391   0.02459  -0.0262   0.0685   1.0000
  10.250   1.1158   0.03597   0.02677  -0.0235   0.0633   1.0000
  10.500   1.1151   0.03805   0.02891  -0.0211   0.0589   1.0000
  10.750   1.1142   0.04032   0.03117  -0.0189   0.0564   1.0000
  11.000   1.1230   0.04223   0.03310  -0.0170   0.0539   1.0000
  11.250   1.1402   0.04384   0.03478  -0.0155   0.0512   1.0000
  11.500   1.1586   0.04550   0.03646  -0.0144   0.0482   1.0000
  11.750   1.2036   0.04801   0.03882  -0.0151   0.0445   1.0000
  12.000   1.2301   0.05050   0.04159  -0.0146   0.0437   1.0000
  12.250   1.2516   0.05348   0.04487  -0.0140   0.0433   1.0000
  12.500   1.2626   0.05675   0.04846  -0.0126   0.0432   1.0000
  12.750   1.2652   0.06006   0.05209  -0.0109   0.0432   1.0000
  13.000   1.2615   0.06345   0.05578  -0.0090   0.0432   1.0000
  13.250   1.2512   0.06677   0.05941  -0.0071   0.0430   1.0000
  13.500   1.2402   0.07048   0.06339  -0.0057   0.0430   1.0000
  13.750   1.2275   0.07457   0.06773  -0.0047   0.0433   1.0000
  14.000   1.2107   0.07879   0.07221  -0.0042   0.0433   1.0000
  14.250   1.1913   0.08342   0.07708  -0.0043   0.0433   1.0000
  14.500   1.1731   0.08849   0.08237  -0.0051   0.0435   1.0000
  14.750   1.1534   0.09395   0.08804  -0.0065   0.0437   1.0000
  15.000   1.1342   0.09993   0.09419  -0.0084   0.0441   1.0000
  15.250   1.1175   0.10641   0.10082  -0.0107   0.0445   1.0000
  15.500   1.1013   0.11313   0.10770  -0.0133   0.0449   1.0000
  15.750   0.8005   0.13384   0.12951  -0.0328   0.0522   1.0000
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