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NACA 0008 (naca0008-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 0008 (naca0008-il)
Reynolds number: 50,000
Max Cl/Cd: 26.12 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca0008-il-50000.txt
Download as CSV file: xf-naca0008-il-50000.csv

 
  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0008                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5182   0.10159   0.09499   0.0193   1.0000   0.3397
  -8.750  -0.5038   0.09681   0.09017   0.0198   1.0000   0.3516
  -8.500  -0.6506   0.10317   0.09637   0.0325   1.0000   0.3419
  -8.250  -0.6331   0.09896   0.09208   0.0341   1.0000   0.3627
  -8.000  -0.6304   0.09544   0.08859   0.0346   1.0000   0.3793
  -7.750  -0.7310   0.07110   0.06426  -0.0072   1.0000   0.1654
  -7.500  -0.7443   0.06103   0.05348  -0.0125   1.0000   0.1393
  -7.250  -0.7331   0.05588   0.04805  -0.0125   1.0000   0.1371
  -7.000  -0.7211   0.05075   0.04259  -0.0123   1.0000   0.1343
  -6.750  -0.7084   0.04576   0.03706  -0.0120   1.0000   0.1319
  -6.500  -0.6931   0.04185   0.03252  -0.0112   1.0000   0.1357
  -6.250  -0.6750   0.03820   0.02823  -0.0102   1.0000   0.1400
  -6.000  -0.6522   0.03505   0.02484  -0.0093   1.0000   0.1443
  -5.750  -0.6298   0.03252   0.02172  -0.0083   1.0000   0.1537
  -5.500  -0.6051   0.03021   0.01927  -0.0076   1.0000   0.1639
  -5.250  -0.5787   0.02786   0.01667  -0.0068   1.0000   0.1729
  -5.000  -0.5518   0.02583   0.01453  -0.0059   1.0000   0.1872
  -4.750  -0.5262   0.02407   0.01284  -0.0050   1.0000   0.2143
  -4.500  -0.5017   0.02218   0.01126  -0.0039   1.0000   0.2658
  -4.250  -0.4840   0.01957   0.00983  -0.0015   1.0000   0.4076
  -4.000  -0.4757   0.01821   0.00959   0.0043   1.0000   0.5930
  -3.750  -0.4640   0.01802   0.00990   0.0111   1.0000   0.7224
  -3.500  -0.4424   0.01845   0.01038   0.0171   1.0000   0.8190
  -3.250  -0.3775   0.01955   0.01096   0.0157   1.0000   0.9067
  -3.000  -0.2313   0.01961   0.01002  -0.0051   1.0000   0.9824
  -2.750  -0.1800   0.01856   0.00864  -0.0123   1.0000   1.0000
  -2.500  -0.1649   0.01782   0.00777  -0.0122   1.0000   1.0000
  -2.250  -0.1490   0.01724   0.00704  -0.0119   1.0000   1.0000
  -2.000  -0.1325   0.01677   0.00647  -0.0112   1.0000   1.0000
  -1.750  -0.1157   0.01641   0.00600  -0.0104   1.0000   1.0000
  -1.500  -0.0988   0.01611   0.00563  -0.0093   1.0000   1.0000
  -1.250  -0.0818   0.01588   0.00532  -0.0081   1.0000   1.0000
  -1.000  -0.0649   0.01571   0.00508  -0.0067   1.0000   1.0000
  -0.750  -0.0483   0.01557   0.00491  -0.0052   1.0000   1.0000
  -0.500  -0.0319   0.01548   0.00479  -0.0035   1.0000   1.0000
  -0.250  -0.0158   0.01543   0.00471  -0.0018   1.0000   1.0000
   0.000   0.0000   0.01541   0.00469   0.0000   1.0000   1.0000
   0.250   0.0158   0.01543   0.00471   0.0018   1.0000   1.0000
   0.500   0.0319   0.01548   0.00479   0.0035   1.0000   1.0000
   0.750   0.0483   0.01557   0.00491   0.0052   1.0000   1.0000
   1.000   0.0649   0.01570   0.00508   0.0067   1.0000   1.0000
   1.250   0.0818   0.01588   0.00532   0.0081   1.0000   1.0000
   1.500   0.0988   0.01611   0.00563   0.0093   1.0000   1.0000
   1.750   0.1158   0.01640   0.00600   0.0104   1.0000   1.0000
   2.000   0.1326   0.01677   0.00647   0.0112   1.0000   1.0000
   2.250   0.1490   0.01724   0.00704   0.0119   1.0000   1.0000
   2.500   0.1649   0.01782   0.00776   0.0122   1.0000   1.0000
   2.750   0.1801   0.01855   0.00863   0.0123   1.0000   1.0000
   3.000   0.2313   0.01961   0.01001   0.0051   0.9825   1.0000
   3.250   0.3775   0.01955   0.01096  -0.0157   0.9067   1.0000
   3.500   0.4424   0.01845   0.01038  -0.0171   0.8190   1.0000
   3.750   0.4640   0.01802   0.00990  -0.0111   0.7224   1.0000
   4.000   0.4757   0.01821   0.00959  -0.0043   0.5930   1.0000
   4.250   0.4840   0.01957   0.00983   0.0015   0.4076   1.0000
   4.500   0.5017   0.02218   0.01125   0.0039   0.2659   1.0000
   4.750   0.5262   0.02407   0.01284   0.0050   0.2143   1.0000
   5.000   0.5518   0.02583   0.01453   0.0059   0.1872   1.0000
   5.250   0.5787   0.02786   0.01667   0.0068   0.1729   1.0000
   5.500   0.6051   0.03021   0.01927   0.0076   0.1639   1.0000
   5.750   0.6298   0.03252   0.02172   0.0083   0.1537   1.0000
   6.000   0.6522   0.03506   0.02484   0.0093   0.1443   1.0000
   6.250   0.6750   0.03820   0.02823   0.0102   0.1400   1.0000
   6.500   0.6931   0.04185   0.03252   0.0112   0.1356   1.0000
   6.750   0.7084   0.04576   0.03706   0.0120   0.1319   1.0000
   7.000   0.7212   0.05075   0.04259   0.0123   0.1343   1.0000
   7.250   0.7331   0.05588   0.04805   0.0125   0.1371   1.0000
   7.500   0.7444   0.06103   0.05348   0.0125   0.1393   1.0000
   7.750   0.7211   0.07403   0.06735   0.0032   0.1842   1.0000
   8.000   0.6308   0.09544   0.08859  -0.0347   0.3792   1.0000
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