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NACA 16-006 (naca16006-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 16-006 (naca16006-il)
Reynolds number: 100,000
Max Cl/Cd: 21.68 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca16006-il-100000-n5.txt
Download as CSV file: xf-naca16006-il-100000-n5.csv

 
  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 16-006                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5185   0.08936   0.08473  -0.0124   1.0000   0.0402
  -8.750  -0.5228   0.08503   0.08043  -0.0138   1.0000   0.0408
  -8.500  -0.5284   0.08061   0.07605  -0.0155   1.0000   0.0412
  -8.250  -0.5359   0.07602   0.07149  -0.0177   1.0000   0.0416
  -8.000  -0.5463   0.07142   0.06692  -0.0204   1.0000   0.0416
  -7.750  -0.5578   0.06730   0.06280  -0.0212   1.0000   0.0417
  -7.500  -0.5666   0.06315   0.05863  -0.0214   1.0000   0.0419
  -7.250  -0.5725   0.05886   0.05427  -0.0214   1.0000   0.0427
  -7.000  -0.5763   0.05458   0.04988  -0.0211   1.0000   0.0436
  -6.000  -0.6046   0.05050   0.04457  -0.0131   1.0000   0.0237
  -5.750  -0.5946   0.04647   0.04027  -0.0111   1.0000   0.0210
  -5.250  -0.5636   0.03910   0.03198  -0.0059   1.0000   0.0166
  -5.000  -0.5497   0.03573   0.02821  -0.0036   1.0000   0.0162
  -4.750  -0.5334   0.03262   0.02468  -0.0014   1.0000   0.0160
  -4.500  -0.5148   0.02973   0.02133   0.0008   1.0000   0.0159
  -4.250  -0.4941   0.02706   0.01818   0.0028   1.0000   0.0159
  -4.000  -0.4711   0.02483   0.01548   0.0045   1.0000   0.0166
  -3.750  -0.4484   0.02253   0.01287   0.0058   1.0000   0.0188
  -3.500  -0.4245   0.02072   0.01085   0.0070   1.0000   0.0205
  -3.250  -0.4011   0.01908   0.00904   0.0084   1.0000   0.0224
  -3.000  -0.3792   0.01784   0.00760   0.0099   1.0000   0.0271
  -2.750  -0.3588   0.01666   0.00632   0.0115   1.0000   0.0340
  -2.500  -0.3377   0.01558   0.00519   0.0129   1.0000   0.0531
  -2.250  -0.1480   0.01275   0.00501  -0.0172   1.0000   1.0000
  -2.000  -0.1300   0.01259   0.00467  -0.0157   1.0000   1.0000
  -1.750  -0.1125   0.01245   0.00434  -0.0141   1.0000   1.0000
  -1.500  -0.0956   0.01233   0.00410  -0.0123   1.0000   1.0000
  -1.250  -0.0791   0.01223   0.00391  -0.0104   1.0000   1.0000
  -1.000  -0.0629   0.01216   0.00376  -0.0084   1.0000   1.0000
  -0.750  -0.0469   0.01210   0.00365  -0.0064   1.0000   1.0000
  -0.500  -0.0311   0.01206   0.00356  -0.0043   1.0000   1.0000
  -0.250  -0.0155   0.01203   0.00351  -0.0022   1.0000   1.0000
   0.000   0.0000   0.01202   0.00349   0.0000   1.0000   1.0000
   0.250   0.0155   0.01203   0.00351   0.0022   1.0000   1.0000
   0.500   0.0311   0.01206   0.00356   0.0043   1.0000   1.0000
   0.750   0.0469   0.01210   0.00365   0.0064   1.0000   1.0000
   1.000   0.0629   0.01216   0.00376   0.0084   1.0000   1.0000
   1.250   0.0791   0.01223   0.00391   0.0104   1.0000   1.0000
   1.500   0.0956   0.01233   0.00410   0.0123   1.0000   1.0000
   1.750   0.1125   0.01245   0.00434   0.0141   1.0000   1.0000
   2.000   0.1299   0.01259   0.00467   0.0157   1.0000   1.0000
   2.250   0.1479   0.01275   0.00501   0.0172   1.0000   1.0000
   2.500   0.3378   0.01558   0.00519  -0.0129   0.0530   1.0000
   2.750   0.3589   0.01666   0.00632  -0.0115   0.0340   1.0000
   3.000   0.3794   0.01784   0.00760  -0.0099   0.0271   1.0000
   3.250   0.4012   0.01909   0.00900  -0.0084   0.0224   1.0000
   3.500   0.4246   0.02072   0.01085  -0.0070   0.0205   1.0000
   3.750   0.4486   0.02254   0.01288  -0.0058   0.0188   1.0000
   4.000   0.4713   0.02484   0.01549  -0.0045   0.0166   1.0000
   4.250   0.4942   0.02707   0.01820  -0.0028   0.0159   1.0000
   4.500   0.5149   0.02973   0.02134  -0.0008   0.0159   1.0000
   4.750   0.5335   0.03262   0.02468   0.0014   0.0160   1.0000
   5.000   0.5498   0.03574   0.02822   0.0036   0.0162   1.0000
   5.250   0.5636   0.03910   0.03199   0.0058   0.0166   1.0000
   5.750   0.5946   0.04647   0.04028   0.0111   0.0210   1.0000
   6.000   0.6046   0.05049   0.04457   0.0131   0.0237   1.0000
   6.500   0.6246   0.06277   0.05690   0.0159   0.0460   1.0000
   6.750   0.6323   0.06373   0.05854   0.0170   0.0413   1.0000
   7.000   0.6378   0.06753   0.06248   0.0173   0.0398   1.0000
   7.250   0.6421   0.07124   0.06627   0.0176   0.0382   1.0000
   7.500   0.5664   0.06299   0.05846   0.0215   0.0422   1.0000
   7.750   0.5573   0.06716   0.06266   0.0213   0.0416   1.0000
   8.000   0.5459   0.07125   0.06675   0.0204   0.0416   1.0000
   8.250   0.5354   0.07586   0.07133   0.0178   0.0416   1.0000
   8.500   0.5280   0.08042   0.07586   0.0156   0.0413   1.0000
   8.750   0.5223   0.08486   0.08027   0.0138   0.0408   1.0000
   9.000   0.5180   0.08916   0.08453   0.0124   0.0403   1.0000
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