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davissm (davissm-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: davissm (davissm-il)
Reynolds number: 100,000
Max Cl/Cd: 70.21 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-davissm-il-100000.txt
Download as CSV file: xf-davissm-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -5.750  -0.3515   0.09520   0.09092  -0.0249   1.0000   0.0500
  -5.500  -0.3508   0.09195   0.08771  -0.0221   1.0000   0.0514
  -5.250  -0.3451   0.08924   0.08502  -0.0221   1.0000   0.0529
  -5.000  -0.3358   0.08655   0.08231  -0.0236   1.0000   0.0546
  -4.750  -0.3226   0.08377   0.07953  -0.0262   1.0000   0.0567
  -4.500  -0.3019   0.08095   0.07668  -0.0312   1.0000   0.0596
  -4.250  -0.2305   0.07882   0.07428  -0.0527   1.0000   0.0625
  -4.000  -0.2359   0.07400   0.06958  -0.0479   1.0000   0.0635
  -3.750  -0.2166   0.06990   0.06549  -0.0486   0.9968   0.0660
  -3.500  -0.1138   0.06682   0.06189  -0.0732   0.9916   0.0766
  -3.250  -0.1104   0.06125   0.05652  -0.0698   0.9883   0.0793
  -3.000  -0.0416   0.05762   0.05257  -0.0837   0.9833   0.0917
  -2.750  -0.0174   0.05395   0.04896  -0.0849   0.9793   0.0965
  -2.500   0.0369   0.05045   0.04525  -0.0939   0.9749   0.1088
  -2.250   0.0844   0.04745   0.04206  -0.1007   0.9700   0.1235
  -2.000   0.1373   0.04481   0.03919  -0.1084   0.9665   0.1510
  -0.500   0.4420   0.03035   0.02225  -0.1395   0.9406   0.1116
  -0.250   0.4915   0.02909   0.02039  -0.1431   0.9369   0.1040
   0.000   0.5264   0.02820   0.01932  -0.1446   0.9290   0.1082
   0.250   0.5740   0.02714   0.01809  -0.1483   0.9251   0.1097
   0.500   0.6069   0.02669   0.01761  -0.1493   0.9167   0.1145
   0.750   0.6521   0.02596   0.01690  -0.1526   0.9117   0.1315
   1.000   0.6901   0.02551   0.01648  -0.1545   0.9043   0.1509
   1.250   0.7346   0.02343   0.01596  -0.1576   0.8992   1.0000
   1.500   0.7841   0.02303   0.01530  -0.1615   0.8953   1.0000
   1.750   0.8121   0.02323   0.01541  -0.1615   0.8840   1.0000
   2.250   0.8875   0.02289   0.01501  -0.1647   0.8684   1.0000
   2.500   0.9166   0.02296   0.01509  -0.1647   0.8577   1.0000
   2.750   0.9596   0.02241   0.01456  -0.1669   0.8522   1.0000
   3.000   0.9863   0.02248   0.01467  -0.1663   0.8403   1.0000
   3.250   1.0150   0.02244   0.01473  -0.1660   0.8291   1.0000
   3.500   1.0484   0.02213   0.01449  -0.1663   0.8197   1.0000
   3.750   1.0850   0.02134   0.01377  -0.1665   0.8091   1.0000
   4.000   1.1116   0.02077   0.01327  -0.1648   0.7913   1.0000
   4.250   1.1397   0.02012   0.01274  -0.1633   0.7731   1.0000
   4.500   1.1685   0.01955   0.01225  -0.1621   0.7556   1.0000
   4.750   1.1957   0.01901   0.01177  -0.1605   0.7344   1.0000
   5.000   1.2214   0.01861   0.01144  -0.1587   0.7104   1.0000
   5.250   1.2447   0.01828   0.01119  -0.1565   0.6790   1.0000
   5.500   1.2651   0.01810   0.01100  -0.1536   0.6354   1.0000
   5.750   1.2799   0.01823   0.01089  -0.1496   0.5615   1.0000
   6.000   1.2796   0.01970   0.01127  -0.1429   0.3874   1.0000
   6.250   1.2646   0.02356   0.01320  -0.1359   0.1428   1.0000
   6.500   1.2691   0.02585   0.01516  -0.1319   0.1109   1.0000
   6.750   1.2742   0.02781   0.01712  -0.1279   0.0982   1.0000
   7.000   1.2804   0.02967   0.01896  -0.1242   0.0878   1.0000
   7.250   1.2922   0.03156   0.02092  -0.1212   0.0799   1.0000
   7.500   1.3206   0.03465   0.02369  -0.1214   0.0720   1.0000
   7.750   1.3443   0.03615   0.02542  -0.1203   0.0657   1.0000
   8.000   1.3809   0.03907   0.02830  -0.1216   0.0611   1.0000
   8.250   1.4235   0.04408   0.03346  -0.1239   0.0587   1.0000
   8.500   1.4402   0.04569   0.03556  -0.1213   0.0565   1.0000
   8.750   1.4592   0.04839   0.03871  -0.1193   0.0546   1.0000
   9.000   1.4784   0.05221   0.04298  -0.1174   0.0550   1.0000
   9.250   1.4939   0.05668   0.04788  -0.1152   0.0563   1.0000
   9.500   1.5192   0.06361   0.05499  -0.1151   0.0596   1.0000
  19.000   0.8809   0.23584   0.23172  -0.1162   0.0693   1.0000
  19.250   0.8809   0.23922   0.23511  -0.1177   0.0665   1.0000
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