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S1010 HPV airfoil (s1010-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S1010 HPV airfoil (s1010-il)
Reynolds number: 200,000
Max Cl/Cd: 40.09 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1010-il-200000-n5.txt
Download as CSV file: xf-s1010-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.7647   0.08244   0.07907   0.0049   1.0000   0.0110
 -10.000  -0.7870   0.07326   0.06996  -0.0012   1.0000   0.0108
  -9.500  -0.8461   0.05123   0.04767  -0.0159   1.0000   0.0100
  -9.250  -0.8638   0.04387   0.03985  -0.0169   1.0000   0.0100
  -9.000  -0.8693   0.03803   0.03343  -0.0164   1.0000   0.0101
  -8.750  -0.8651   0.03347   0.02828  -0.0153   1.0000   0.0105
  -8.500  -0.8536   0.03011   0.02440  -0.0141   1.0000   0.0110
  -8.250  -0.8385   0.02734   0.02118  -0.0130   1.0000   0.0115
  -8.000  -0.8211   0.02546   0.01910  -0.0122   1.0000   0.0129
  -7.750  -0.7994   0.02453   0.01802  -0.0116   1.0000   0.0145
  -7.500  -0.7783   0.02302   0.01621  -0.0108   1.0000   0.0162
  -7.250  -0.7565   0.02153   0.01440  -0.0098   1.0000   0.0174
  -7.000  -0.7364   0.01972   0.01243  -0.0089   1.0000   0.0195
  -6.750  -0.7126   0.01910   0.01167  -0.0083   1.0000   0.0225
  -6.500  -0.6890   0.01821   0.01059  -0.0076   1.0000   0.0250
  -6.250  -0.6662   0.01712   0.00934  -0.0067   1.0000   0.0269
  -6.000  -0.6430   0.01627   0.00844  -0.0059   1.0000   0.0308
  -5.750  -0.6189   0.01564   0.00770  -0.0052   1.0000   0.0354
  -5.500  -0.5955   0.01485   0.00684  -0.0044   1.0000   0.0403
  -5.250  -0.5714   0.01429   0.00622  -0.0037   1.0000   0.0475
  -5.000  -0.5474   0.01375   0.00563  -0.0030   1.0000   0.0558
  -4.750  -0.5231   0.01332   0.00516  -0.0023   1.0000   0.0647
  -4.500  -0.4988   0.01295   0.00480  -0.0016   1.0000   0.0766
  -4.250  -0.4747   0.01260   0.00448  -0.0009   1.0000   0.0906
  -4.000  -0.4507   0.01226   0.00416  -0.0002   1.0000   0.1036
  -3.750  -0.4268   0.01193   0.00384   0.0006   1.0000   0.1169
  -3.500  -0.4030   0.01162   0.00354   0.0014   1.0000   0.1299
  -3.250  -0.3793   0.01132   0.00324   0.0022   1.0000   0.1443
  -3.000  -0.3557   0.01102   0.00301   0.0030   1.0000   0.1633
  -2.750  -0.3323   0.01073   0.00280   0.0039   1.0000   0.1861
  -2.500  -0.3090   0.01044   0.00261   0.0047   1.0000   0.2131
  -2.250  -0.2861   0.01012   0.00245   0.0056   1.0000   0.2508
  -2.000  -0.2637   0.00975   0.00229   0.0065   1.0000   0.3027
  -1.750  -0.2421   0.00931   0.00217   0.0076   1.0000   0.3789
  -1.500  -0.2219   0.00875   0.00207   0.0089   1.0000   0.4897
  -1.250  -0.2053   0.00803   0.00208   0.0113   1.0000   0.6531
  -1.000  -0.1884   0.00770   0.00225   0.0142   1.0000   0.7959
  -0.750  -0.1653   0.00766   0.00237   0.0158   1.0000   0.8636
  -0.500  -0.1048   0.00770   0.00246   0.0095   0.9850   0.9129
  -0.250  -0.0475   0.00771   0.00247   0.0038   0.9700   0.9382
   0.000   0.0000   0.00771   0.00247   0.0000   0.9559   0.9559
   0.250   0.0476   0.00771   0.00247  -0.0038   0.9381   0.9700
   0.500   0.1048   0.00770   0.00246  -0.0095   0.9130   0.9851
   0.750   0.1651   0.00766   0.00237  -0.0157   0.8639   1.0000
   1.000   0.1882   0.00770   0.00224  -0.0142   0.7951   1.0000
   1.250   0.2052   0.00803   0.00208  -0.0112   0.6532   1.0000
   1.500   0.2218   0.00875   0.00207  -0.0089   0.4901   1.0000
   1.750   0.2419   0.00931   0.00216  -0.0075   0.3798   1.0000
   2.000   0.2635   0.00975   0.00228  -0.0065   0.3030   1.0000
   2.250   0.2859   0.01012   0.00245  -0.0055   0.2508   1.0000
   2.500   0.3088   0.01044   0.00261  -0.0047   0.2133   1.0000
   2.750   0.3320   0.01073   0.00280  -0.0038   0.1862   1.0000
   3.000   0.3555   0.01102   0.00301  -0.0030   0.1634   1.0000
   3.250   0.3790   0.01132   0.00324  -0.0022   0.1443   1.0000
   3.500   0.4027   0.01162   0.00354  -0.0014   0.1300   1.0000
   3.750   0.4266   0.01193   0.00384  -0.0006   0.1169   1.0000
   4.000   0.4505   0.01226   0.00415   0.0002   0.1037   1.0000
   4.250   0.4745   0.01260   0.00448   0.0009   0.0907   1.0000
   4.500   0.4987   0.01295   0.00479   0.0016   0.0766   1.0000
   4.750   0.5229   0.01332   0.00516   0.0023   0.0649   1.0000
   5.000   0.5472   0.01375   0.00563   0.0030   0.0559   1.0000
   5.250   0.5713   0.01429   0.00622   0.0037   0.0475   1.0000
   5.500   0.5954   0.01485   0.00684   0.0044   0.0403   1.0000
   5.750   0.6189   0.01564   0.00770   0.0052   0.0354   1.0000
   6.000   0.6430   0.01626   0.00843   0.0059   0.0308   1.0000
   6.250   0.6662   0.01713   0.00935   0.0067   0.0269   1.0000
   6.500   0.6891   0.01822   0.01059   0.0075   0.0250   1.0000
   6.750   0.7127   0.01911   0.01167   0.0083   0.0225   1.0000
   7.000   0.7366   0.01971   0.01242   0.0088   0.0195   1.0000
   7.250   0.7567   0.02154   0.01441   0.0098   0.0174   1.0000
   7.500   0.7786   0.02302   0.01622   0.0107   0.0162   1.0000
   7.750   0.7997   0.02459   0.01809   0.0116   0.0145   1.0000
   8.000   0.8219   0.02528   0.01888   0.0120   0.0127   1.0000
   8.250   0.8390   0.02735   0.02118   0.0129   0.0115   1.0000
   8.500   0.8541   0.03014   0.02443   0.0140   0.0110   1.0000
   8.750   0.8655   0.03354   0.02836   0.0152   0.0105   1.0000
   9.000   0.8699   0.03805   0.03345   0.0162   0.0102   1.0000
   9.250   0.8641   0.04398   0.03996   0.0167   0.0100   1.0000
   9.500   0.8472   0.05120   0.04764   0.0158   0.0101   1.0000
  10.000   0.7888   0.07315   0.06986   0.0010   0.0108   1.0000
  10.250   0.7661   0.08246   0.07909  -0.0052   0.0110   1.0000
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