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davissm (davissm-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: davissm (davissm-il)
Reynolds number: 200,000
Max Cl/Cd: 92.47 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-davissm-il-200000-n5.txt
Download as CSV file: xf-davissm-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3202   0.11623   0.11263  -0.0345   1.0000   0.0193
  -8.750  -0.3263   0.11490   0.11137  -0.0329   1.0000   0.0193
  -8.500  -0.3262   0.11289   0.10940  -0.0332   0.9985   0.0193
  -8.250  -0.3135   0.10948   0.10599  -0.0375   0.9936   0.0194
  -8.000  -0.3003   0.10601   0.10252  -0.0418   0.9867   0.0194
  -7.750  -0.2824   0.10201   0.09852  -0.0470   0.9807   0.0194
  -7.500  -0.2619   0.09781   0.09431  -0.0525   0.9768   0.0195
  -7.250  -0.2500   0.09272   0.08923  -0.0526   0.9735   0.0197
  -7.000  -0.2344   0.08855   0.08505  -0.0538   0.9705   0.0201
  -6.750  -0.2137   0.08473   0.08121  -0.0578   0.9677   0.0206
  -6.500  -0.1893   0.08087   0.07732  -0.0633   0.9653   0.0212
  -6.250  -0.1664   0.07729   0.07372  -0.0683   0.9600   0.0220
  -6.000  -0.1378   0.07341   0.06980  -0.0750   0.9563   0.0233
  -5.750  -0.0755   0.06912   0.06537  -0.0941   0.9529   0.0263
  -5.500  -0.0409   0.06489   0.06107  -0.1014   0.9483   0.0264
  -5.250  -0.0064   0.06055   0.05665  -0.1081   0.9439   0.0264
  -5.000   0.0314   0.05605   0.05205  -0.1152   0.9406   0.0264
  -4.750   0.0715   0.05144   0.04732  -0.1225   0.9380   0.0265
  -4.500   0.1047   0.04726   0.04302  -0.1275   0.9322   0.0264
  -4.250   0.1253   0.04361   0.03936  -0.1293   0.9276   0.0248
  -3.750   0.2238   0.03428   0.02949  -0.1450   0.9199   0.0261
  -3.500   0.2624   0.03033   0.02529  -0.1497   0.9149   0.0257
  -3.250   0.3054   0.02629   0.02084  -0.1543   0.9110   0.0260
  -3.000   0.3381   0.02425   0.01857  -0.1567   0.9056   0.0283
  -2.750   0.3708   0.02245   0.01652  -0.1584   0.8998   0.0297
  -2.500   0.4074   0.01991   0.01351  -0.1605   0.8954   0.0298
  -2.250   0.4386   0.01824   0.01147  -0.1613   0.8889   0.0306
  -2.000   0.4697   0.01698   0.00987  -0.1620   0.8832   0.0319
  -1.750   0.4995   0.01624   0.00883  -0.1622   0.8773   0.0348
  -1.500   0.5284   0.01544   0.00778  -0.1623   0.8706   0.0356
  -1.250   0.5579   0.01466   0.00680  -0.1625   0.8648   0.0366
  -1.000   0.5854   0.01392   0.00599  -0.1625   0.8572   0.0385
  -0.750   0.6140   0.01356   0.00559  -0.1626   0.8510   0.0415
  -0.500   0.6412   0.01329   0.00529  -0.1624   0.8428   0.0452
  -0.250   0.6696   0.01296   0.00490  -0.1624   0.8362   0.0475
   0.000   0.6970   0.01265   0.00460  -0.1623   0.8279   0.0502
   0.250   0.7249   0.01245   0.00440  -0.1623   0.8204   0.0559
   0.500   0.7525   0.01232   0.00425  -0.1621   0.8117   0.0633
   0.750   0.7801   0.01217   0.00412  -0.1620   0.8028   0.0747
   1.000   0.8081   0.01195   0.00405  -0.1620   0.7944   0.1314
   1.500   0.8617   0.01049   0.00412  -0.1618   0.7748   1.0000
   1.750   0.8891   0.01057   0.00412  -0.1616   0.7650   1.0000
   2.000   0.9160   0.01067   0.00418  -0.1613   0.7538   1.0000
   2.250   0.9428   0.01078   0.00424  -0.1610   0.7421   1.0000
   2.500   0.9696   0.01090   0.00431  -0.1606   0.7294   1.0000
   2.750   0.9957   0.01102   0.00436  -0.1601   0.7121   1.0000
   3.000   1.0212   0.01118   0.00445  -0.1594   0.6897   1.0000
   3.250   1.0461   0.01137   0.00453  -0.1587   0.6640   1.0000
   3.500   1.0711   0.01159   0.00467  -0.1579   0.6395   1.0000
   3.750   1.0958   0.01185   0.00485  -0.1572   0.6142   1.0000
   4.000   1.1193   0.01219   0.00505  -0.1562   0.5821   1.0000
   4.250   1.1418   0.01259   0.00534  -0.1550   0.5445   1.0000
   4.500   1.1634   0.01308   0.00566  -0.1538   0.5031   1.0000
   4.750   1.1828   0.01374   0.00605  -0.1521   0.4483   1.0000
   5.000   1.1990   0.01469   0.00660  -0.1500   0.3722   1.0000
   5.250   1.2105   0.01615   0.00741  -0.1473   0.2601   1.0000
   5.500   1.2134   0.01867   0.00890  -0.1435   0.0890   1.0000
   5.750   1.2324   0.01951   0.00968  -0.1420   0.0709   1.0000
   6.000   1.2522   0.02023   0.01043  -0.1407   0.0605   1.0000
   6.250   1.2723   0.02087   0.01114  -0.1393   0.0521   1.0000
   6.500   1.2906   0.02165   0.01194  -0.1377   0.0445   1.0000
   6.750   1.3091   0.02235   0.01275  -0.1362   0.0385   1.0000
   7.000   1.3250   0.02324   0.01367  -0.1342   0.0336   1.0000
   7.250   1.3415   0.02401   0.01453  -0.1322   0.0297   1.0000
   7.500   1.3546   0.02502   0.01558  -0.1298   0.0270   1.0000
   7.750   1.3645   0.02624   0.01689  -0.1267   0.0252   1.0000
   8.000   1.3754   0.02734   0.01812  -0.1238   0.0238   1.0000
   8.250   1.3849   0.02841   0.01932  -0.1208   0.0221   1.0000
   8.500   1.3954   0.02943   0.02041  -0.1181   0.0204   1.0000
   8.750   1.4029   0.03077   0.02180  -0.1150   0.0191   1.0000
   9.000   1.4082   0.03254   0.02366  -0.1116   0.0183   1.0000
   9.250   1.4181   0.03402   0.02530  -0.1090   0.0177   1.0000
   9.500   1.4287   0.03563   0.02707  -0.1066   0.0169   1.0000
   9.750   1.4401   0.03734   0.02895  -0.1043   0.0162   1.0000
  10.000   1.4523   0.03911   0.03091  -0.1022   0.0156   1.0000
  10.250   1.4630   0.04069   0.03263  -0.1001   0.0147   1.0000
  10.500   1.4717   0.04220   0.03426  -0.0980   0.0140   1.0000
  10.750   1.4789   0.04397   0.03612  -0.0958   0.0133   1.0000
  11.000   1.4868   0.04675   0.03910  -0.0937   0.0127   1.0000
  11.250   1.4946   0.04916   0.04181  -0.0914   0.0124   1.0000
  11.500   1.4993   0.05200   0.04499  -0.0890   0.0121   1.0000
  11.750   1.5000   0.05523   0.04856  -0.0864   0.0118   1.0000
  12.000   1.4962   0.05887   0.05256  -0.0836   0.0115   1.0000
  12.250   1.4881   0.06283   0.05686  -0.0809   0.0113   1.0000
  12.500   1.4765   0.06711   0.06150  -0.0785   0.0112   1.0000
  12.750   1.4621   0.07170   0.06640  -0.0765   0.0110   1.0000
  13.000   1.4459   0.07656   0.07155  -0.0750   0.0109   1.0000
  13.250   1.4279   0.08185   0.07711  -0.0743   0.0107   1.0000
  13.500   1.4082   0.08762   0.08313  -0.0743   0.0107   1.0000
  13.750   1.3879   0.09379   0.08955  -0.0752   0.0106   1.0000
  14.000   1.3662   0.10070   0.09669  -0.0771   0.0105   1.0000
  14.250   1.3407   0.10906   0.10526  -0.0804   0.0107   1.0000
  14.500   1.3164   0.11805   0.11447  -0.0849   0.0108   1.0000
  14.750   1.2898   0.12879   0.12540  -0.0913   0.0111   1.0000
  15.000   1.2642   0.14080   0.13758  -0.0993   0.0113   1.0000
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