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S9027 (8%) (s9027-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S9027 (8%) (s9027-il)
Reynolds number: 100,000
Max Cl/Cd: 30.64 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s9027-il-100000.txt
Download as CSV file: xf-s9027-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S9027 (8%)                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.7039   0.10193   0.09703   0.0072   1.0000   0.1488
  -9.250  -0.6720   0.09736   0.09236   0.0120   1.0000   0.1514
  -9.000  -0.7887   0.06659   0.06148  -0.0151   1.0000   0.0794
  -8.750  -0.7941   0.06107   0.05581  -0.0159   1.0000   0.0786
  -8.500  -0.7991   0.05538   0.04984  -0.0164   1.0000   0.0778
  -8.250  -0.8007   0.04973   0.04377  -0.0164   1.0000   0.0769
  -8.000  -0.7972   0.04436   0.03791  -0.0159   1.0000   0.0760
  -7.750  -0.7888   0.03958   0.03257  -0.0149   1.0000   0.0758
  -7.500  -0.7757   0.03562   0.02803  -0.0138   1.0000   0.0768
  -7.250  -0.7589   0.03248   0.02425  -0.0125   1.0000   0.0791
  -7.000  -0.7397   0.02988   0.02138  -0.0116   1.0000   0.0836
  -6.750  -0.7174   0.02811   0.01944  -0.0108   1.0000   0.0889
  -6.500  -0.6947   0.02612   0.01688  -0.0095   1.0000   0.0941
  -6.250  -0.6715   0.02427   0.01512  -0.0089   1.0000   0.1022
  -6.000  -0.6482   0.02285   0.01359  -0.0081   1.0000   0.1131
  -5.750  -0.6242   0.02145   0.01209  -0.0072   1.0000   0.1249
  -5.500  -0.6006   0.02043   0.01108  -0.0064   1.0000   0.1403
  -5.250  -0.5768   0.01941   0.01007  -0.0056   1.0000   0.1573
  -5.000  -0.5531   0.01847   0.00910  -0.0048   1.0000   0.1780
  -4.750  -0.5297   0.01750   0.00827  -0.0039   1.0000   0.2008
  -4.500  -0.5065   0.01665   0.00755  -0.0030   1.0000   0.2300
  -4.250  -0.4835   0.01581   0.00686  -0.0020   1.0000   0.2638
  -4.000  -0.4610   0.01505   0.00632  -0.0009   1.0000   0.3051
  -3.750  -0.4390   0.01432   0.00586   0.0002   1.0000   0.3524
  -3.500  -0.4173   0.01365   0.00549   0.0015   1.0000   0.4088
  -3.250  -0.3963   0.01302   0.00520   0.0031   1.0000   0.4725
  -3.000  -0.3757   0.01245   0.00498   0.0049   1.0000   0.5428
  -2.750  -0.3556   0.01196   0.00481   0.0070   1.0000   0.6165
  -2.500  -0.3356   0.01156   0.00472   0.0094   1.0000   0.6911
  -2.250  -0.3151   0.01128   0.00470   0.0121   1.0000   0.7655
  -2.000  -0.2915   0.01114   0.00474   0.0144   1.0000   0.8373
  -1.750  -0.2499   0.01124   0.00485   0.0134   1.0000   0.9039
  -1.500  -0.1857   0.01147   0.00493   0.0073   1.0000   0.9525
  -1.250  -0.1066   0.01153   0.00479  -0.0026   1.0000   0.9838
  -1.000  -0.0512   0.01127   0.00441  -0.0088   1.0000   1.0000
  -0.750  -0.0395   0.01104   0.00416  -0.0067   1.0000   1.0000
  -0.500  -0.0270   0.01089   0.00399  -0.0044   1.0000   1.0000
  -0.250  -0.0139   0.01081   0.00390  -0.0022   1.0000   1.0000
   0.000   0.0000   0.01078   0.00387   0.0000   1.0000   1.0000
   0.250   0.0139   0.01081   0.00390   0.0022   1.0000   1.0000
   0.500   0.0270   0.01089   0.00399   0.0044   1.0000   1.0000
   0.750   0.0395   0.01104   0.00416   0.0066   1.0000   1.0000
   1.000   0.0512   0.01127   0.00441   0.0088   1.0000   1.0000
   1.250   0.1064   0.01153   0.00478   0.0026   0.9839   1.0000
   1.500   0.1855   0.01147   0.00492  -0.0072   0.9526   1.0000
   1.750   0.2499   0.01124   0.00484  -0.0134   0.9037   1.0000
   2.000   0.2913   0.01114   0.00473  -0.0144   0.8372   1.0000
   2.250   0.3148   0.01128   0.00469  -0.0120   0.7656   1.0000
   2.500   0.3353   0.01156   0.00472  -0.0094   0.6913   1.0000
   2.750   0.3553   0.01196   0.00481  -0.0070   0.6167   1.0000
   3.000   0.3755   0.01245   0.00498  -0.0048   0.5430   1.0000
   3.250   0.3960   0.01302   0.00519  -0.0030   0.4729   1.0000
   3.500   0.4171   0.01365   0.00548  -0.0015   0.4089   1.0000
   3.750   0.4388   0.01432   0.00586  -0.0002   0.3526   1.0000
   4.000   0.4607   0.01505   0.00631   0.0010   0.3053   1.0000
   4.250   0.4833   0.01581   0.00686   0.0020   0.2639   1.0000
   4.500   0.5064   0.01665   0.00755   0.0030   0.2300   1.0000
   4.750   0.5295   0.01750   0.00826   0.0039   0.2008   1.0000
   5.000   0.5529   0.01847   0.00910   0.0048   0.1781   1.0000
   5.250   0.5767   0.01940   0.01006   0.0056   0.1572   1.0000
   5.500   0.6006   0.02042   0.01107   0.0065   0.1403   1.0000
   5.750   0.6241   0.02145   0.01209   0.0072   0.1249   1.0000
   6.000   0.6482   0.02286   0.01359   0.0081   0.1131   1.0000
   6.250   0.6716   0.02427   0.01513   0.0089   0.1022   1.0000
   6.500   0.6948   0.02614   0.01690   0.0095   0.0940   1.0000
   6.750   0.7175   0.02811   0.01944   0.0107   0.0888   1.0000
   7.000   0.7398   0.02991   0.02141   0.0116   0.0837   1.0000
   7.250   0.7591   0.03249   0.02426   0.0124   0.0791   1.0000
   7.500   0.7760   0.03564   0.02805   0.0137   0.0768   1.0000
   7.750   0.7892   0.03960   0.03260   0.0149   0.0758   1.0000
   8.000   0.7975   0.04440   0.03795   0.0158   0.0760   1.0000
   8.250   0.8010   0.04980   0.04384   0.0163   0.0769   1.0000
   8.500   0.7994   0.05546   0.04993   0.0163   0.0777   1.0000
   8.750   0.7946   0.06114   0.05588   0.0157   0.0786   1.0000
   9.000   0.7892   0.06668   0.06157   0.0149   0.0794   1.0000
   9.250   0.6736   0.09744   0.09246  -0.0122   0.1513   1.0000
   9.500   0.7065   0.10200   0.09711  -0.0072   0.1489   1.0000
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