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davissm (davissm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: davissm (davissm-il)
Reynolds number: 1,000,000
Max Cl/Cd: 128.83 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-davissm-il-1000000-n5.txt
Download as CSV file: xf-davissm-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.1989   0.08749   0.08561  -0.0669   0.9390   0.0064
  -7.750  -0.1900   0.08455   0.08264  -0.0688   0.9276   0.0066
  -7.500  -0.1793   0.08147   0.07953  -0.0714   0.9183   0.0068
  -7.250  -0.1656   0.07820   0.07622  -0.0747   0.9100   0.0067
  -7.000  -0.1503   0.07473   0.07273  -0.0785   0.9024   0.0065
  -6.500  -0.1127   0.06712   0.06503  -0.0881   0.8884   0.0065
  -6.250  -0.0894   0.06270   0.06056  -0.0942   0.8818   0.0067
  -6.000  -0.0586   0.05598   0.05377  -0.1040   0.8755   0.0075
  -4.500   0.1999   0.01206   0.00757  -0.1597   0.8454   0.0137
  -4.250   0.2284   0.01138   0.00669  -0.1601   0.8398   0.0142
  -4.000   0.2571   0.01055   0.00563  -0.1605   0.8344   0.0146
  -3.750   0.2857   0.00988   0.00479  -0.1608   0.8284   0.0153
  -3.500   0.3138   0.00965   0.00448  -0.1610   0.8223   0.0158
  -3.250   0.3421   0.00945   0.00422  -0.1611   0.8154   0.0164
  -3.000   0.3701   0.00931   0.00401  -0.1611   0.8084   0.0172
  -2.750   0.3983   0.00908   0.00371  -0.1613   0.8009   0.0180
  -2.500   0.4263   0.00883   0.00337  -0.1613   0.7939   0.0187
  -2.250   0.4545   0.00863   0.00310  -0.1614   0.7866   0.0191
  -2.000   0.4825   0.00847   0.00287  -0.1615   0.7792   0.0194
  -1.750   0.5106   0.00812   0.00244  -0.1616   0.7708   0.0206
  -1.500   0.5385   0.00801   0.00230  -0.1616   0.7618   0.0217
  -1.000   0.5940   0.00792   0.00214  -0.1616   0.7417   0.0244
  -0.750   0.6218   0.00787   0.00203  -0.1616   0.7321   0.0254
  -0.500   0.6494   0.00784   0.00195  -0.1615   0.7220   0.0261
  -0.250   0.6771   0.00777   0.00183  -0.1615   0.7109   0.0276
   0.000   0.7048   0.00773   0.00176  -0.1615   0.6992   0.0301
   0.250   0.7322   0.00774   0.00175  -0.1614   0.6869   0.0328
   0.500   0.7595   0.00778   0.00173  -0.1613   0.6739   0.0348
   0.750   0.7868   0.00782   0.00173  -0.1612   0.6603   0.0362
   1.000   0.8140   0.00785   0.00174  -0.1611   0.6464   0.0427
   1.250   0.8403   0.00798   0.00179  -0.1608   0.6229   0.0504
   1.500   0.8661   0.00814   0.00187  -0.1605   0.5903   0.0728
   1.750   0.8926   0.00818   0.00197  -0.1603   0.5691   0.1492
   2.000   0.9190   0.00818   0.00212  -0.1602   0.5488   0.2621
   2.250   0.9443   0.00819   0.00234  -0.1599   0.5165   0.4368
   2.750   0.9946   0.00772   0.00266  -0.1593   0.4572   1.0000
   3.000   1.0203   0.00801   0.00283  -0.1589   0.4290   1.0000
   3.250   1.0450   0.00841   0.00304  -0.1584   0.3914   1.0000
   3.500   1.0686   0.00891   0.00330  -0.1578   0.3412   1.0000
   3.750   1.0898   0.00970   0.00369  -0.1567   0.2652   1.0000
   4.000   1.1032   0.01143   0.00456  -0.1544   0.0919   1.0000
   4.250   1.1276   0.01182   0.00486  -0.1538   0.0705   1.0000
   4.500   1.1527   0.01212   0.00511  -0.1534   0.0608   1.0000
   4.750   1.1779   0.01240   0.00536  -0.1530   0.0527   1.0000
   5.000   1.2028   0.01269   0.00561  -0.1525   0.0452   1.0000
   5.250   1.2277   0.01297   0.00588  -0.1521   0.0396   1.0000
   5.500   1.2523   0.01328   0.00616  -0.1516   0.0338   1.0000
   5.750   1.2765   0.01361   0.00646  -0.1510   0.0278   1.0000
   6.000   1.3005   0.01394   0.00677  -0.1504   0.0231   1.0000
   6.250   1.3240   0.01433   0.00712  -0.1497   0.0184   1.0000
   6.500   1.3477   0.01466   0.00748  -0.1491   0.0166   1.0000
   6.750   1.3706   0.01505   0.00787  -0.1483   0.0145   1.0000
   7.000   1.3931   0.01548   0.00831  -0.1474   0.0127   1.0000
   7.250   1.4159   0.01585   0.00872  -0.1466   0.0119   1.0000
   7.500   1.4379   0.01626   0.00918  -0.1456   0.0110   1.0000
   7.750   1.4592   0.01671   0.00965  -0.1446   0.0102   1.0000
   8.000   1.4794   0.01724   0.01019  -0.1433   0.0093   1.0000
   8.250   1.4989   0.01779   0.01080  -0.1419   0.0086   1.0000
   8.500   1.5188   0.01827   0.01133  -0.1406   0.0083   1.0000
   8.750   1.5377   0.01879   0.01191  -0.1391   0.0080   1.0000
   9.000   1.5557   0.01934   0.01253  -0.1374   0.0076   1.0000
   9.250   1.5731   0.01991   0.01314  -0.1357   0.0072   1.0000
   9.500   1.5896   0.02049   0.01376  -0.1338   0.0068   1.0000
   9.750   1.6044   0.02116   0.01447  -0.1316   0.0064   1.0000
  10.000   1.6148   0.02203   0.01542  -0.1286   0.0060   1.0000
  10.250   1.6230   0.02291   0.01638  -0.1252   0.0058   1.0000
  10.500   1.6341   0.02366   0.01722  -0.1224   0.0057   1.0000
  10.750   1.6444   0.02450   0.01814  -0.1196   0.0056   1.0000
  11.000   1.6546   0.02540   0.01912  -0.1170   0.0054   1.0000
  11.250   1.6647   0.02635   0.02015  -0.1144   0.0052   1.0000
  11.500   1.6741   0.02739   0.02127  -0.1119   0.0050   1.0000
  11.750   1.6829   0.02852   0.02249  -0.1094   0.0049   1.0000
  12.000   1.6914   0.02971   0.02377  -0.1070   0.0047   1.0000
  12.250   1.6997   0.03094   0.02508  -0.1047   0.0045   1.0000
  12.500   1.7074   0.03226   0.02651  -0.1025   0.0044   1.0000
  12.750   1.7145   0.03368   0.02801  -0.1002   0.0042   1.0000
  13.000   1.7209   0.03519   0.02960  -0.0981   0.0041   1.0000
  13.250   1.7254   0.03690   0.03141  -0.0959   0.0039   1.0000
  13.500   1.7272   0.03895   0.03356  -0.0935   0.0038   1.0000
  13.750   1.7238   0.04156   0.03633  -0.0909   0.0036   1.0000
  14.000   1.7282   0.04344   0.03831  -0.0892   0.0035   1.0000
  14.250   1.7311   0.04552   0.04051  -0.0874   0.0035   1.0000
  14.500   1.7344   0.04761   0.04270  -0.0859   0.0034   1.0000
  14.750   1.7350   0.05007   0.04528  -0.0844   0.0034   1.0000
  15.000   1.7351   0.05263   0.04797  -0.0830   0.0033   1.0000
  15.250   1.7341   0.05541   0.05087  -0.0818   0.0032   1.0000
  15.500   1.7316   0.05848   0.05409  -0.0807   0.0032   1.0000
  15.750   1.7279   0.06181   0.05755  -0.0799   0.0031   1.0000
  16.000   1.7236   0.06533   0.06122  -0.0792   0.0030   1.0000
  16.250   1.7187   0.06903   0.06504  -0.0789   0.0030   1.0000
  16.500   1.7125   0.07305   0.06921  -0.0787   0.0029   1.0000
  16.750   1.7044   0.07750   0.07380  -0.0789   0.0029   1.0000
  17.000   1.6960   0.08214   0.07858  -0.0794   0.0028   1.0000
  17.250   1.6860   0.08715   0.08373  -0.0801   0.0028   1.0000
  17.500   1.6756   0.09237   0.08909  -0.0812   0.0027   1.0000
  17.750   1.6644   0.09786   0.09473  -0.0826   0.0027   1.0000
  18.000   1.6498   0.10415   0.10117  -0.0846   0.0027   1.0000
  18.250   1.6353   0.11060   0.10776  -0.0869   0.0027   1.0000
  18.500   1.6199   0.11737   0.11468  -0.0896   0.0027   1.0000
  18.750   1.6026   0.12472   0.12219  -0.0929   0.0026   1.0000
  19.000   1.5845   0.13251   0.13012  -0.0967   0.0026   1.0000
  19.250   1.5628   0.14144   0.13922  -0.1014   0.0026   1.0000
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