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NACA 8-H-12 AIRFOIL (n8h12-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 8-H-12 AIRFOIL (n8h12-il)
Reynolds number: 50,000
Max Cl/Cd: 7.96 at α=-0.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n8h12-il-50000.txt
Download as CSV file: xf-n8h12-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 8-H-12 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4328   0.11751   0.11197   0.0027   1.0000   0.2154
  -9.500  -0.4072   0.11189   0.10636   0.0024   1.0000   0.2245
  -9.250  -0.4291   0.11149   0.10612  -0.0034   1.0000   0.2324
  -9.000  -0.3999   0.10582   0.10045  -0.0033   1.0000   0.2469
  -8.750  -0.3805   0.10132   0.09598  -0.0045   1.0000   0.2596
  -8.500  -0.3691   0.09774   0.09246  -0.0065   1.0000   0.2743
  -8.250  -0.3599   0.09454   0.08933  -0.0084   1.0000   0.2923
  -8.000  -0.3561   0.09189   0.08677  -0.0105   1.0000   0.3113
  -7.750  -0.3608   0.08998   0.08497  -0.0118   1.0000   0.3294
  -7.500  -0.3625   0.08813   0.08322  -0.0104   1.0000   0.3455
  -7.250  -0.3639   0.08648   0.08165  -0.0069   1.0000   0.3592
  -6.750  -0.3281   0.08019   0.07536  -0.0104   0.9770   0.4268
  -6.500  -0.2669   0.07487   0.06995  -0.0124   0.9701   0.4884
  -6.000  -0.1647   0.06616   0.06105  -0.0166   0.9508   0.6182
  -5.250  -0.2822   0.04999   0.04313  -0.0578   0.8987   0.1794
  -5.000  -0.2718   0.04745   0.04002  -0.0565   0.8880   0.1645
  -4.750  -0.2575   0.04502   0.03714  -0.0552   0.8785   0.1561
  -4.500  -0.2331   0.04289   0.03435  -0.0548   0.8702   0.1490
  -4.250  -0.2206   0.04145   0.03260  -0.0528   0.8604   0.1468
  -4.000  -0.2006   0.04013   0.03085  -0.0517   0.8522   0.1480
  -3.750  -0.1791   0.03903   0.02930  -0.0506   0.8441   0.1503
  -3.500  -0.1592   0.03815   0.02801  -0.0493   0.8362   0.1518
  -3.250  -0.1307   0.03678   0.02657  -0.0496   0.8288   0.1571
  -3.000  -0.1092   0.03628   0.02584  -0.0488   0.8216   0.1656
  -2.750   0.1648   0.02789   0.02031  -0.0832   0.8159   1.0000
  -2.500   0.1814   0.02850   0.02054  -0.0823   0.8086   1.0000
  -2.250   0.1954   0.02921   0.02097  -0.0815   0.8007   1.0000
  -2.000   0.2131   0.02986   0.02133  -0.0804   0.7944   1.0000
  -1.750   0.2227   0.03082   0.02210  -0.0794   0.7877   1.0000
  -1.500   0.2387   0.03160   0.02265  -0.0783   0.7818   1.0000
  -1.250   0.2501   0.03257   0.02343  -0.0770   0.7763   1.0000
  -1.000   0.2565   0.03364   0.02435  -0.0753   0.7705   1.0000
  -0.750   0.2703   0.03460   0.02514  -0.0740   0.7661   1.0000
  -0.500   0.2839   0.03565   0.02601  -0.0728   0.7621   1.0000
  -0.250   0.2793   0.03699   0.02725  -0.0698   0.7583   1.0000
   0.000   0.2802   0.03823   0.02836  -0.0672   0.7549   1.0000
   0.250   0.2831   0.03947   0.02948  -0.0649   0.7528   1.0000
   0.500   0.2856   0.04075   0.03063  -0.0624   0.7513   1.0000
   0.750   0.2883   0.04200   0.03177  -0.0599   0.7500   1.0000
   1.000   0.2787   0.04329   0.03295  -0.0559   0.7508   1.0000
   1.250   0.2648   0.04464   0.03421  -0.0517   0.7554   1.0000
   1.500   0.2677   0.04604   0.03550  -0.0497   0.7592   1.0000
   1.750   0.2763   0.04753   0.03690  -0.0487   0.7643   1.0000
   3.000   0.1440   0.04958   0.03869  -0.0227   0.9484   1.0000
   3.250   0.1802   0.05204   0.04106  -0.0262   0.9290   1.0000
   3.500   0.2126   0.05448   0.04343  -0.0289   0.9126   1.0000
   3.750   0.2407   0.05675   0.04564  -0.0307   0.8976   1.0000
   4.000   0.2570   0.05796   0.04682  -0.0304   0.8810   1.0000
   4.250   0.2781   0.05974   0.04856  -0.0310   0.8662   1.0000
   4.500   0.3010   0.06181   0.05061  -0.0319   0.8534   1.0000
   4.750   0.3280   0.06431   0.05309  -0.0335   0.8408   1.0000
   5.000   0.3493   0.06627   0.05506  -0.0340   0.8267   1.0000
   5.250   0.3636   0.06764   0.05644  -0.0335   0.8127   1.0000
   5.500   0.3779   0.06917   0.05798  -0.0331   0.7987   1.0000
   5.750   0.3921   0.07085   0.05968  -0.0327   0.7856   1.0000
   6.000   0.4091   0.07289   0.06174  -0.0328   0.7736   1.0000
   6.250   0.4395   0.07618   0.06508  -0.0348   0.7626   1.0000
   6.500   0.4542   0.07785   0.06679  -0.0345   0.7483   1.0000
   6.750   0.4640   0.07930   0.06830  -0.0336   0.7341   1.0000
   7.000   0.4742   0.08105   0.07009  -0.0330   0.7209   1.0000
   7.250   0.4878   0.08320   0.07230  -0.0328   0.7080   1.0000
   7.500   0.5074   0.08595   0.07512  -0.0334   0.6963   1.0000
   7.750   0.5382   0.08967   0.07898  -0.0351   0.6831   1.0000
   8.250   0.5505   0.09277   0.08221  -0.0333   0.6539   1.0000
   8.500   0.5592   0.09488   0.08439  -0.0328   0.6397   1.0000
   8.750   0.5694   0.09724   0.08684  -0.0326   0.6256   1.0000
   9.000   0.5810   0.09977   0.08949  -0.0325   0.6111   1.0000
   9.250   0.5928   0.10240   0.09222  -0.0325   0.5964   1.0000
   9.500   0.6046   0.10505   0.09497  -0.0324   0.5810   1.0000
   9.750   0.6157   0.10773   0.09776  -0.0323   0.5651   1.0000
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