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S1010 HPV airfoil (s1010-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S1010 HPV airfoil (s1010-il)
Reynolds number: 50,000
Max Cl/Cd: 20.44 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1010-il-50000.txt
Download as CSV file: xf-s1010-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.6435   0.11260   0.10562   0.0268   1.0000   0.2467
  -9.000  -0.6664   0.11141   0.10458   0.0237   1.0000   0.2548
  -8.750  -0.6523   0.10653   0.09967   0.0246   1.0000   0.2680
  -8.500  -0.6401   0.10195   0.09508   0.0252   1.0000   0.2801
  -8.250  -0.6413   0.09861   0.09181   0.0250   1.0000   0.2951
  -8.000  -0.6460   0.09564   0.08892   0.0248   1.0000   0.3102
  -7.750  -0.6299   0.09143   0.08468   0.0271   1.0000   0.3364
  -7.500  -0.6283   0.08782   0.08113   0.0278   1.0000   0.3553
  -7.250  -0.6164   0.08390   0.07719   0.0291   1.0000   0.3747
  -6.750  -0.6751   0.05763   0.05013  -0.0106   1.0000   0.1420
  -6.500  -0.6642   0.05253   0.04468  -0.0112   1.0000   0.1417
  -6.250  -0.6513   0.04763   0.03927  -0.0114   1.0000   0.1422
  -6.000  -0.6352   0.04291   0.03402  -0.0111   1.0000   0.1420
  -5.750  -0.6172   0.03854   0.02894  -0.0104   1.0000   0.1438
  -5.500  -0.5971   0.03583   0.02589  -0.0095   1.0000   0.1567
  -5.250  -0.5752   0.03300   0.02284  -0.0085   1.0000   0.1688
  -5.000  -0.5530   0.03054   0.01996  -0.0075   1.0000   0.1854
  -4.750  -0.5295   0.02830   0.01761  -0.0065   1.0000   0.2032
  -4.500  -0.5057   0.02646   0.01548  -0.0055   1.0000   0.2260
  -4.250  -0.4810   0.02462   0.01363  -0.0046   1.0000   0.2483
  -4.000  -0.4562   0.02304   0.01201  -0.0037   1.0000   0.2765
  -3.750  -0.4304   0.02157   0.01050  -0.0028   1.0000   0.3112
  -3.500  -0.4045   0.02012   0.00924  -0.0019   1.0000   0.3569
  -3.250  -0.3802   0.01860   0.00809  -0.0007   1.0000   0.4240
  -3.000  -0.2216   0.01642   0.00733  -0.0162   1.0000   1.0000
  -2.750  -0.2042   0.01601   0.00661  -0.0153   1.0000   1.0000
  -2.500  -0.1857   0.01570   0.00606  -0.0143   1.0000   1.0000
  -2.250  -0.1668   0.01545   0.00560  -0.0132   1.0000   1.0000
  -2.000  -0.1477   0.01525   0.00522  -0.0121   1.0000   1.0000
  -1.750  -0.1287   0.01507   0.00487  -0.0108   1.0000   1.0000
  -1.500  -0.1097   0.01493   0.00461  -0.0095   1.0000   1.0000
  -1.250  -0.0909   0.01481   0.00439  -0.0080   1.0000   1.0000
  -1.000  -0.0723   0.01472   0.00422  -0.0066   1.0000   1.0000
  -0.750  -0.0539   0.01465   0.00409  -0.0050   1.0000   1.0000
  -0.500  -0.0357   0.01460   0.00399  -0.0034   1.0000   1.0000
  -0.250  -0.0178   0.01457   0.00393  -0.0017   1.0000   1.0000
   0.000   0.0000   0.01456   0.00391   0.0000   1.0000   1.0000
   0.250   0.0178   0.01457   0.00393   0.0017   1.0000   1.0000
   0.500   0.0357   0.01460   0.00399   0.0034   1.0000   1.0000
   0.750   0.0539   0.01465   0.00409   0.0050   1.0000   1.0000
   1.000   0.0723   0.01472   0.00422   0.0066   1.0000   1.0000
   1.250   0.0909   0.01481   0.00439   0.0080   1.0000   1.0000
   1.500   0.1097   0.01493   0.00461   0.0095   1.0000   1.0000
   1.750   0.1287   0.01507   0.00487   0.0108   1.0000   1.0000
   2.000   0.1478   0.01525   0.00522   0.0121   1.0000   1.0000
   2.250   0.1668   0.01545   0.00560   0.0132   1.0000   1.0000
   2.500   0.1858   0.01570   0.00605   0.0143   1.0000   1.0000
   2.750   0.2043   0.01600   0.00661   0.0153   1.0000   1.0000
   3.000   0.2217   0.01641   0.00733   0.0161   1.0000   1.0000
   3.250   0.3802   0.01860   0.00809   0.0007   0.4242   1.0000
   3.500   0.4045   0.02012   0.00924   0.0019   0.3569   1.0000
   3.750   0.4305   0.02157   0.01050   0.0028   0.3111   1.0000
   4.000   0.4562   0.02304   0.01201   0.0036   0.2766   1.0000
   4.250   0.4810   0.02463   0.01363   0.0046   0.2482   1.0000
   4.500   0.5057   0.02646   0.01548   0.0055   0.2260   1.0000
   4.750   0.5296   0.02830   0.01761   0.0065   0.2033   1.0000
   5.000   0.5530   0.03053   0.01996   0.0075   0.1855   1.0000
   5.250   0.5753   0.03300   0.02284   0.0085   0.1688   1.0000
   5.500   0.5971   0.03582   0.02589   0.0095   0.1567   1.0000
   5.750   0.6172   0.03853   0.02894   0.0104   0.1439   1.0000
   6.000   0.6352   0.04291   0.03402   0.0111   0.1420   1.0000
   6.250   0.6514   0.04762   0.03927   0.0114   0.1422   1.0000
   6.500   0.6644   0.05253   0.04468   0.0112   0.1417   1.0000
   6.750   0.6754   0.05763   0.05013   0.0106   0.1421   1.0000
   7.000   0.6870   0.06475   0.05755   0.0091   0.1573   1.0000
   7.250   0.6170   0.08391   0.07720  -0.0291   0.3744   1.0000
   7.500   0.6320   0.08811   0.08143  -0.0277   0.3547   1.0000
   7.750   0.6320   0.09159   0.08484  -0.0271   0.3369   1.0000
   8.000   0.6477   0.09574   0.08901  -0.0249   0.3103   1.0000
   8.250   0.6413   0.09860   0.09179  -0.0252   0.2950   1.0000
   8.500   0.6410   0.10198   0.09512  -0.0253   0.2801   1.0000
   8.750   0.6516   0.10645   0.09958  -0.0248   0.2678   1.0000
   9.000   0.6670   0.11142   0.10458  -0.0238   0.2548   1.0000
   9.250   0.6444   0.11265   0.10566  -0.0269   0.2464   1.0000
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