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davissm (davissm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: davissm (davissm-il)
Reynolds number: 1,000,000
Max Cl/Cd: 154.72 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-davissm-il-1000000.txt
Download as CSV file: xf-davissm-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3273   0.11739   0.11573  -0.0321   1.0000   0.0081
  -9.500  -0.3234   0.11492   0.11328  -0.0322   1.0000   0.0082
  -9.250  -0.3201   0.11253   0.11091  -0.0323   0.9998   0.0085
  -9.000  -0.3057   0.10890   0.10727  -0.0358   0.9987   0.0089
  -8.750  -0.2907   0.10514   0.10350  -0.0394   0.9967   0.0097
  -8.500  -0.2778   0.10154   0.09991  -0.0429   0.9833   0.0104
  -8.250  -0.2628   0.09775   0.09612  -0.0477   0.9772   0.0105
  -8.000  -0.2461   0.09389   0.09225  -0.0526   0.9735   0.0105
  -7.750  -0.2253   0.08971   0.08805  -0.0586   0.9703   0.0105
  -7.500  -0.1987   0.08521   0.08353  -0.0660   0.9679   0.0105
  -6.500  -0.1067   0.06984   0.06803  -0.0869   0.9428   0.0116
  -6.250  -0.0845   0.06666   0.06480  -0.0916   0.9350   0.0120
  -6.000  -0.0614   0.06340   0.06150  -0.0963   0.9273   0.0126
  -5.500   0.0074   0.05510   0.05307  -0.1125   0.9137   0.0143
  -5.250   0.0410   0.05078   0.04866  -0.1192   0.9080   0.0144
  -5.000   0.0724   0.04497   0.04278  -0.1266   0.9021   0.0149
  -4.750   0.0983   0.04287   0.04062  -0.1291   0.8967   0.0153
  -4.500   0.1287   0.04049   0.03817  -0.1328   0.8916   0.0160
  -4.250   0.1643   0.03760   0.03520  -0.1375   0.8863   0.0179
  -4.000   0.2124   0.03361   0.03102  -0.1442   0.8817   0.0193
  -3.750   0.2543   0.02890   0.02611  -0.1496   0.8770   0.0194
  -3.500   0.2951   0.02273   0.01961  -0.1558   0.8721   0.0207
  -3.250   0.3237   0.02172   0.01848  -0.1569   0.8667   0.0216
  -3.000   0.3549   0.02029   0.01693  -0.1581   0.8609   0.0242
  -2.750   0.3799   0.00407   0.00037  -0.1535   0.8420   0.0240
  -2.500   0.4287   0.01205   0.00752  -0.1624   0.8511   0.0226
  -2.250   0.4582   0.01095   0.00622  -0.1628   0.8452   0.0234
  -2.000   0.4869   0.01026   0.00536  -0.1630   0.8393   0.0246
  -1.750   0.5154   0.00981   0.00479  -0.1631   0.8330   0.0256
  -1.500   0.5435   0.00954   0.00444  -0.1631   0.8260   0.0262
  -1.250   0.5718   0.00882   0.00359  -0.1632   0.8193   0.0270
  -1.000   0.5999   0.00817   0.00286  -0.1633   0.8121   0.0290
  -0.750   0.6279   0.00805   0.00273  -0.1634   0.8051   0.0310
  -0.500   0.6558   0.00789   0.00253  -0.1634   0.7974   0.0328
  -0.250   0.6837   0.00776   0.00236  -0.1634   0.7896   0.0345
   0.000   0.7114   0.00768   0.00225  -0.1633   0.7812   0.0357
   0.250   0.7394   0.00747   0.00199  -0.1633   0.7722   0.0390
   0.500   0.7670   0.00742   0.00192  -0.1633   0.7631   0.0434
   0.750   0.7945   0.00739   0.00186  -0.1632   0.7530   0.0467
   1.000   0.8222   0.00735   0.00180  -0.1631   0.7426   0.0543
   1.250   0.8492   0.00726   0.00180  -0.1630   0.7271   0.1132
   1.500   0.8753   0.00686   0.00198  -0.1630   0.7088   0.4377
   1.750   0.9012   0.00587   0.00203  -0.1628   0.6947   1.0000
   2.000   0.9282   0.00600   0.00209  -0.1627   0.6786   1.0000
   2.250   0.9546   0.00617   0.00216  -0.1623   0.6562   1.0000
   2.500   0.9807   0.00636   0.00224  -0.1620   0.6340   1.0000
   2.750   1.0070   0.00655   0.00234  -0.1617   0.6127   1.0000
   3.000   1.0330   0.00677   0.00247  -0.1614   0.5902   1.0000
   3.250   1.0584   0.00704   0.00261  -0.1609   0.5604   1.0000
   3.500   1.0831   0.00739   0.00279  -0.1603   0.5235   1.0000
   3.750   1.1064   0.00788   0.00303  -0.1595   0.4702   1.0000
   4.000   1.1294   0.00842   0.00332  -0.1587   0.4154   1.0000
   4.250   1.1515   0.00907   0.00366  -0.1578   0.3530   1.0000
   4.500   1.1702   0.01009   0.00418  -0.1563   0.2565   1.0000
   4.750   1.1809   0.01205   0.00521  -0.1535   0.0811   1.0000
   5.000   1.2049   0.01246   0.00555  -0.1529   0.0657   1.0000
   5.250   1.2295   0.01278   0.00586  -0.1523   0.0571   1.0000
   5.500   1.2538   0.01313   0.00617  -0.1518   0.0489   1.0000
   5.750   1.2783   0.01342   0.00647  -0.1513   0.0426   1.0000
   6.000   1.3019   0.01382   0.00681  -0.1506   0.0341   1.0000
   6.250   1.3246   0.01430   0.00723  -0.1497   0.0259   1.0000
   6.500   1.3482   0.01464   0.00760  -0.1490   0.0228   1.0000
   6.750   1.3690   0.01530   0.00827  -0.1477   0.0184   1.0000
   7.000   1.3919   0.01567   0.00868  -0.1469   0.0172   1.0000
   7.250   1.4137   0.01613   0.00918  -0.1459   0.0158   1.0000
   7.500   1.4342   0.01670   0.00977  -0.1446   0.0145   1.0000
   7.750   1.4481   0.01783   0.01104  -0.1420   0.0128   1.0000
   8.000   1.4690   0.01826   0.01150  -0.1408   0.0125   1.0000
   8.250   1.4880   0.01881   0.01212  -0.1393   0.0119   1.0000
   8.500   1.5056   0.01945   0.01282  -0.1375   0.0113   1.0000
   8.750   1.5221   0.02011   0.01354  -0.1355   0.0108   1.0000
   9.000   1.5384   0.02076   0.01424  -0.1336   0.0103   1.0000
   9.250   1.5528   0.02149   0.01501  -0.1313   0.0098   1.0000
   9.500   1.5587   0.02275   0.01636  -0.1275   0.0092   1.0000
   9.750   1.5533   0.02467   0.01845  -0.1216   0.0087   1.0000
  10.000   1.5663   0.02535   0.01921  -0.1192   0.0086   1.0000
  10.250   1.5778   0.02620   0.02013  -0.1166   0.0084   1.0000
  10.500   1.5882   0.02717   0.02119  -0.1140   0.0081   1.0000
  10.750   1.5968   0.02835   0.02247  -0.1112   0.0078   1.0000
  11.000   1.6056   0.02955   0.02378  -0.1086   0.0075   1.0000
  11.250   1.6149   0.03072   0.02503  -0.1063   0.0072   1.0000
  11.500   1.6237   0.03194   0.02632  -0.1040   0.0069   1.0000
  11.750   1.6310   0.03334   0.02782  -0.1016   0.0067   1.0000
  12.000   1.6374   0.03487   0.02943  -0.0992   0.0065   1.0000
  12.250   1.6411   0.03669   0.03135  -0.0967   0.0063   1.0000
  12.500   1.6385   0.03931   0.03413  -0.0935   0.0061   1.0000
  12.750   1.6200   0.04423   0.03941  -0.0887   0.0058   1.0000
  13.000   1.6272   0.04565   0.04092  -0.0872   0.0057   1.0000
  13.250   1.6307   0.04763   0.04302  -0.0854   0.0056   1.0000
  13.500   1.6336   0.04972   0.04525  -0.0838   0.0055   1.0000
  13.750   1.6340   0.05215   0.04782  -0.0821   0.0054   1.0000
  14.000   1.6317   0.05497   0.05080  -0.0805   0.0052   1.0000
  14.250   1.6253   0.05843   0.05443  -0.0789   0.0051   1.0000
  14.500   1.6192   0.06196   0.05812  -0.0777   0.0050   1.0000
  14.750   1.6088   0.06619   0.06254  -0.0767   0.0050   1.0000
  15.000   1.5988   0.07055   0.06707  -0.0762   0.0049   1.0000
  15.250   1.5871   0.07539   0.07209  -0.0761   0.0048   1.0000
  15.500   1.5738   0.08070   0.07757  -0.0765   0.0048   1.0000
  15.750   1.5556   0.08705   0.08412  -0.0775   0.0047   1.0000
  16.000   1.5392   0.09345   0.09070  -0.0791   0.0047   1.0000
  16.250   1.5201   0.10071   0.09814  -0.0815   0.0047   1.0000
  16.500   1.4992   0.10870   0.10632  -0.0847   0.0047   1.0000
  16.750   1.4742   0.11794   0.11576  -0.0889   0.0047   1.0000
  17.000   1.4462   0.12856   0.12658  -0.0945   0.0047   1.0000
  17.250   1.4173   0.14025   0.13846  -0.1013   0.0048   1.0000
  17.500   1.3812   0.15511   0.15354  -0.1107   0.0049   1.0000
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