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davissm (davissm-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: davissm (davissm-il)
Reynolds number: 200,000
Max Cl/Cd: 96.47 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-davissm-il-200000.txt
Download as CSV file: xf-davissm-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: davissm                                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3373   0.11287   0.10946  -0.0272   1.0000   0.0259
  -8.000  -0.3522   0.11273   0.10940  -0.0238   1.0000   0.0260
  -7.750  -0.3684   0.11265   0.10939  -0.0202   1.0000   0.0261
  -7.500  -0.3783   0.11198   0.10879  -0.0187   1.0000   0.0261
  -7.250  -0.3709   0.10986   0.10669  -0.0225   0.9985   0.0262
  -7.000  -0.3413   0.10569   0.10249  -0.0320   0.9949   0.0264
  -6.750  -0.3130   0.10135   0.09812  -0.0400   0.9909   0.0264
  -6.500  -0.3014   0.09457   0.09136  -0.0409   0.9886   0.0269
  -6.250  -0.2878   0.08977   0.08656  -0.0403   0.9864   0.0275
  -6.000  -0.2681   0.08580   0.08257  -0.0433   0.9822   0.0282
  -5.750  -0.2407   0.08171   0.07844  -0.0490   0.9791   0.0293
  -5.500  -0.2120   0.07776   0.07445  -0.0553   0.9750   0.0307
  -5.250  -0.1789   0.07371   0.07037  -0.0628   0.9704   0.0328
  -5.000  -0.0919   0.06980   0.06622  -0.0870   0.9673   0.0361
  -4.750  -0.0520   0.06317   0.05952  -0.0958   0.9657   0.0367
  -4.500  -0.0416   0.05929   0.05567  -0.0948   0.9597   0.0376
  -4.250  -0.0123   0.05578   0.05212  -0.0983   0.9567   0.0392
  -4.000   0.0309   0.05199   0.04824  -0.1055   0.9546   0.0418
  -3.750   0.1172   0.04798   0.04379  -0.1227   0.9535   0.0484
  -3.500   0.1515   0.04231   0.03812  -0.1281   0.9524   0.0507
  -3.250   0.1775   0.04011   0.03590  -0.1297   0.9462   0.0538
  -3.000   0.2490   0.03792   0.03301  -0.1399   0.9442   0.0624
  -2.750   0.2810   0.03287   0.02813  -0.1441   0.9425   0.0658
  -2.500   0.3353   0.03008   0.02488  -0.1507   0.9414   0.0778
  -2.250   0.3801   0.02792   0.02251  -0.1554   0.9402   0.0921
  -2.000   0.4199   0.02566   0.02027  -0.1591   0.9388   0.1000
  -1.250   0.5440   0.01959   0.01274  -0.1660   0.9265   0.0772
  -1.000   0.5846   0.01736   0.01025  -0.1684   0.9240   0.0676
  -0.750   0.6125   0.01655   0.00919  -0.1679   0.9158   0.0661
  -0.500   0.6476   0.01576   0.00831  -0.1692   0.9112   0.0688
  -0.250   0.6759   0.01538   0.00788  -0.1690   0.9038   0.0741
   0.000   0.7071   0.01489   0.00732  -0.1694   0.8976   0.0765
   0.250   0.7354   0.01430   0.00683  -0.1693   0.8902   0.0824
   0.500   0.7649   0.01394   0.00651  -0.1694   0.8830   0.0942
   0.750   0.7923   0.01367   0.00631  -0.1691   0.8746   0.1141
   1.000   0.8217   0.01185   0.00616  -0.1694   0.8679   1.0000
   1.250   0.8479   0.01192   0.00612  -0.1688   0.8585   1.0000
   1.500   0.8771   0.01188   0.00597  -0.1686   0.8517   1.0000
   1.750   0.9025   0.01195   0.00600  -0.1679   0.8411   1.0000
   2.000   0.9292   0.01198   0.00601  -0.1674   0.8316   1.0000
   2.250   0.9575   0.01195   0.00592  -0.1671   0.8233   1.0000
   2.500   0.9831   0.01199   0.00595  -0.1664   0.8115   1.0000
   2.750   1.0091   0.01195   0.00589  -0.1656   0.7982   1.0000
   3.000   1.0350   0.01187   0.00580  -0.1647   0.7828   1.0000
   3.250   1.0608   0.01183   0.00571  -0.1638   0.7666   1.0000
   3.500   1.0864   0.01187   0.00575  -0.1630   0.7505   1.0000
   3.750   1.1114   0.01193   0.00582  -0.1621   0.7319   1.0000
   4.000   1.1365   0.01199   0.00587  -0.1612   0.7108   1.0000
   4.250   1.1609   0.01211   0.00598  -0.1601   0.6869   1.0000
   4.500   1.1847   0.01228   0.00610  -0.1590   0.6594   1.0000
   4.750   1.2072   0.01253   0.00624  -0.1575   0.6245   1.0000
   5.000   1.2275   0.01293   0.00645  -0.1557   0.5750   1.0000
   5.250   1.2442   0.01361   0.00683  -0.1532   0.5041   1.0000
   5.500   1.2510   0.01511   0.00753  -0.1490   0.3683   1.0000
   5.750   1.2413   0.01864   0.00936  -0.1430   0.1128   1.0000
   6.000   1.2536   0.02018   0.01074  -0.1402   0.0851   1.0000
   6.250   1.2661   0.02155   0.01214  -0.1375   0.0715   1.0000
   6.500   1.2802   0.02269   0.01334  -0.1350   0.0621   1.0000
   6.750   1.2914   0.02409   0.01479  -0.1320   0.0551   1.0000
   7.000   1.3049   0.02522   0.01595  -0.1296   0.0489   1.0000
   7.250   1.3144   0.02707   0.01783  -0.1264   0.0452   1.0000
   7.500   1.3308   0.02833   0.01919  -0.1242   0.0421   1.0000
   7.750   1.3479   0.02968   0.02060  -0.1223   0.0391   1.0000
   8.000   1.3725   0.03261   0.02346  -0.1223   0.0352   1.0000
   8.250   1.3940   0.03384   0.02492  -0.1210   0.0338   1.0000
   8.500   1.4221   0.03604   0.02732  -0.1208   0.0323   1.0000
   8.750   1.4508   0.03888   0.03043  -0.1206   0.0314   1.0000
   9.000   1.4732   0.04151   0.03332  -0.1196   0.0302   1.0000
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