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S1010 HPV airfoil (s1010-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S1010 HPV airfoil (s1010-il)
Reynolds number: 50,000
Max Cl/Cd: 21.32 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1010-il-50000-n5.txt
Download as CSV file: xf-s1010-il-50000-n5.csv

 
  
       XFOIL         Version 6.96
  
 Calculated polar for: S1010 HPV airfoil                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.6956   0.08977   0.08290   0.0008   1.0000   0.0477
  -9.000  -0.7024   0.08373   0.07692  -0.0037   1.0000   0.0474
  -8.750  -0.7118   0.07798   0.07119  -0.0071   1.0000   0.0471
  -8.500  -0.7202   0.07210   0.06525  -0.0100   1.0000   0.0468
  -8.250  -0.7271   0.06630   0.05931  -0.0122   1.0000   0.0468
  -8.000  -0.7318   0.06047   0.05323  -0.0137   1.0000   0.0470
  -7.750  -0.7338   0.05456   0.04689  -0.0146   1.0000   0.0479
  -7.500  -0.7287   0.05007   0.04202  -0.0147   1.0000   0.0504
  -7.250  -0.7134   0.04823   0.04009  -0.0142   1.0000   0.0551
  -7.000  -0.7028   0.04366   0.03495  -0.0137   1.0000   0.0573
  -6.750  -0.6888   0.03914   0.02970  -0.0130   1.0000   0.0595
  -6.500  -0.6708   0.03543   0.02538  -0.0120   1.0000   0.0624
  -6.250  -0.6502   0.03326   0.02302  -0.0112   1.0000   0.0669
  -6.000  -0.6286   0.03116   0.02047  -0.0104   1.0000   0.0760
  -5.750  -0.6060   0.02941   0.01845  -0.0096   1.0000   0.0851
  -5.500  -0.5829   0.02780   0.01668  -0.0088   1.0000   0.0955
  -5.250  -0.5594   0.02645   0.01505  -0.0080   1.0000   0.1094
  -5.000  -0.5351   0.02510   0.01354  -0.0073   1.0000   0.1235
  -4.750  -0.5105   0.02399   0.01221  -0.0065   1.0000   0.1412
  -4.500  -0.4854   0.02283   0.01103  -0.0058   1.0000   0.1565
  -4.250  -0.4609   0.02192   0.01010  -0.0051   1.0000   0.1782
  -4.000  -0.4355   0.02097   0.00914  -0.0046   1.0000   0.2000
  -3.750  -0.4109   0.02010   0.00832  -0.0040   1.0000   0.2289
  -3.500  -0.3879   0.01925   0.00749  -0.0031   1.0000   0.2631
  -3.250  -0.3661   0.01834   0.00683  -0.0021   1.0000   0.3100
  -3.000  -0.3461   0.01732   0.00625  -0.0007   1.0000   0.3856
  -2.750  -0.3299   0.01611   0.00585   0.0019   1.0000   0.5261
  -2.500  -0.2998   0.01536   0.00607   0.0044   1.0000   0.7959
  -2.250  -0.2438   0.01540   0.00585   0.0009   1.0000   0.9200
  -2.000  -0.1644   0.01529   0.00533  -0.0087   1.0000   0.9866
  -1.750  -0.1283   0.01509   0.00490  -0.0109   1.0000   1.0000
  -1.500  -0.1094   0.01494   0.00461  -0.0095   1.0000   1.0000
  -1.250  -0.0907   0.01482   0.00439  -0.0081   1.0000   1.0000
  -1.000  -0.0721   0.01473   0.00422  -0.0066   1.0000   1.0000
  -0.750  -0.0538   0.01466   0.00409  -0.0050   1.0000   1.0000
  -0.500  -0.0357   0.01460   0.00399  -0.0034   1.0000   1.0000
  -0.250  -0.0177   0.01457   0.00394  -0.0017   1.0000   1.0000
   0.000   0.0000   0.01456   0.00392   0.0000   1.0000   1.0000
   0.250   0.0177   0.01457   0.00394   0.0017   1.0000   1.0000
   0.500   0.0357   0.01460   0.00399   0.0034   1.0000   1.0000
   0.750   0.0538   0.01465   0.00409   0.0050   1.0000   1.0000
   1.000   0.0721   0.01473   0.00422   0.0066   1.0000   1.0000
   1.250   0.0907   0.01482   0.00439   0.0081   1.0000   1.0000
   1.500   0.1095   0.01494   0.00461   0.0095   1.0000   1.0000
   1.750   0.1284   0.01508   0.00490   0.0108   1.0000   1.0000
   2.000   0.1641   0.01529   0.00532   0.0088   0.9868   1.0000
   2.250   0.2439   0.01539   0.00585  -0.0009   0.9200   1.0000
   2.500   0.2997   0.01536   0.00607  -0.0044   0.7963   1.0000
   2.750   0.3298   0.01611   0.00585  -0.0019   0.5266   1.0000
   3.000   0.3460   0.01732   0.00625   0.0007   0.3858   1.0000
   3.250   0.3660   0.01834   0.00683   0.0021   0.3100   1.0000
   3.500   0.3878   0.01925   0.00748   0.0031   0.2633   1.0000
   3.750   0.4109   0.02010   0.00831   0.0040   0.2289   1.0000
   4.000   0.4355   0.02097   0.00914   0.0046   0.2002   1.0000
   4.250   0.4609   0.02192   0.01010   0.0052   0.1783   1.0000
   4.500   0.4854   0.02283   0.01102   0.0058   0.1564   1.0000
   4.750   0.5105   0.02399   0.01220   0.0065   0.1412   1.0000
   5.000   0.5351   0.02510   0.01354   0.0073   0.1235   1.0000
   5.250   0.5594   0.02646   0.01505   0.0081   0.1094   1.0000
   5.500   0.5829   0.02781   0.01669   0.0088   0.0954   1.0000
   5.750   0.6060   0.02941   0.01845   0.0096   0.0851   1.0000
   6.000   0.6287   0.03117   0.02048   0.0104   0.0760   1.0000
   6.250   0.6503   0.03326   0.02302   0.0112   0.0668   1.0000
   6.500   0.6710   0.03543   0.02538   0.0120   0.0624   1.0000
   6.750   0.6890   0.03916   0.02972   0.0129   0.0595   1.0000
   7.000   0.7031   0.04368   0.03497   0.0137   0.0573   1.0000
   7.250   0.7137   0.04826   0.04012   0.0141   0.0550   1.0000
   7.500   0.7292   0.05003   0.04196   0.0147   0.0503   1.0000
   7.750   0.7340   0.05464   0.04697   0.0145   0.0479   1.0000
   8.000   0.7322   0.06055   0.05331   0.0136   0.0470   1.0000
   8.250   0.7276   0.06637   0.05939   0.0120   0.0468   1.0000
   8.500   0.7207   0.07219   0.06534   0.0098   0.0468   1.0000
   8.750   0.7122   0.07812   0.07133   0.0068   0.0471   1.0000
   9.000   0.7031   0.08384   0.07703   0.0034   0.0474   1.0000
   9.250   0.6965   0.08987   0.08300  -0.0010   0.0477   1.0000
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