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NACA M16 AIRFOIL (m16-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA M16 AIRFOIL (m16-il)
Reynolds number: 1,000,000
Max Cl/Cd: 102.95 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m16-il-1000000-n5.txt
Download as CSV file: xf-m16-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M16 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.5403   0.10608   0.10402   0.0297   0.7567   0.0028
  -8.250  -0.5382   0.10184   0.09974   0.0276   0.7429   0.0028
  -8.000  -0.5364   0.09780   0.09567   0.0251   0.7299   0.0029
  -7.750  -0.5334   0.09434   0.09219   0.0226   0.7175   0.0030
  -7.500  -0.5244   0.09055   0.08835   0.0188   0.7062   0.0031
  -7.250  -0.5136   0.08649   0.08425   0.0148   0.6961   0.0032
  -7.000  -0.5007   0.08232   0.08003   0.0108   0.6863   0.0033
  -6.750  -0.4862   0.07772   0.07537   0.0065   0.6781   0.0034
  -6.250  -0.4513   0.06665   0.06414  -0.0032   0.6638   0.0041
  -6.000  -0.4302   0.05571   0.05302  -0.0111   0.6590   0.0046
  -5.750  -0.4059   0.04976   0.04690  -0.0149   0.6531   0.0051
  -5.500  -0.3810   0.04574   0.04273  -0.0172   0.6463   0.0055
  -5.000  -0.3284   0.03104   0.02729  -0.0219   0.6361   0.0071
  -4.750  -0.3018   0.02805   0.02412  -0.0224   0.6298   0.0084
  -4.500  -0.2751   0.02533   0.02119  -0.0228   0.6243   0.0097
  -4.250  -0.2485   0.01972   0.01508  -0.0229   0.6195   0.0118
  -4.000  -0.2242   0.01234   0.00662  -0.0227   0.6149   0.0170
  -3.750  -0.1962   0.01208   0.00627  -0.0228   0.6094   0.0175
  -3.500  -0.1676   0.01249   0.00671  -0.0229   0.6032   0.0184
  -3.250  -0.1392   0.01289   0.00714  -0.0231   0.5976   0.0191
  -3.000  -0.1110   0.01312   0.00737  -0.0232   0.5920   0.0199
  -2.750  -0.0828   0.01288   0.00703  -0.0233   0.5861   0.0207
  -2.500  -0.0547   0.01251   0.00657  -0.0234   0.5810   0.0217
  -2.250  -0.0265   0.01193   0.00586  -0.0235   0.5754   0.0228
  -1.750   0.0300   0.01096   0.00466  -0.0236   0.5645   0.0253
  -1.500   0.0584   0.01079   0.00443  -0.0238   0.5585   0.0263
  -1.250   0.0867   0.01072   0.00431  -0.0239   0.5529   0.0271
  -1.000   0.1151   0.01067   0.00422  -0.0240   0.5466   0.0276
  -0.500   0.1717   0.01018   0.00362  -0.0243   0.5344   0.0289
  -0.250   0.1996   0.00961   0.00296  -0.0244   0.5281   0.0298
   0.000   0.2278   0.00930   0.00262  -0.0245   0.5217   0.0302
   0.250   0.2560   0.00908   0.00236  -0.0246   0.5147   0.0303
   0.500   0.2843   0.00888   0.00214  -0.0248   0.5082   0.0303
   0.750   0.3125   0.00870   0.00194  -0.0249   0.5006   0.0312
   1.000   0.3409   0.00857   0.00178  -0.0251   0.4936   0.0312
   1.250   0.3693   0.00847   0.00165  -0.0252   0.4861   0.0308
   1.500   0.3977   0.00839   0.00156  -0.0254   0.4788   0.0305
   1.750   0.4262   0.00834   0.00148  -0.0256   0.4709   0.0302
   2.000   0.4546   0.00829   0.00143  -0.0258   0.4638   0.0300
   2.250   0.4831   0.00827   0.00139  -0.0260   0.4558   0.0298
   2.500   0.5115   0.00825   0.00137  -0.0262   0.4485   0.0296
   2.750   0.5400   0.00825   0.00136  -0.0264   0.4410   0.0296
   3.000   0.5684   0.00825   0.00137  -0.0267   0.4334   0.0296
   3.250   0.5969   0.00829   0.00139  -0.0269   0.4263   0.0298
   3.500   0.6253   0.00833   0.00142  -0.0271   0.4168   0.0306
   3.750   0.6535   0.00846   0.00150  -0.0274   0.3938   0.0363
   4.250   0.7052   0.00685   0.00187  -0.0274   0.3469   1.0000
   4.500   0.7327   0.00728   0.00208  -0.0277   0.2995   1.0000
   4.750   0.7593   0.00813   0.00251  -0.0282   0.2060   1.0000
   5.000   0.7837   0.01004   0.00354  -0.0290   0.0163   1.0000
   5.250   0.8112   0.01028   0.00380  -0.0291   0.0125   1.0000
   5.500   0.8385   0.01055   0.00411  -0.0293   0.0104   1.0000
   5.750   0.8656   0.01096   0.00454  -0.0294   0.0078   1.0000
   6.000   0.8927   0.01124   0.00485  -0.0295   0.0071   1.0000
   6.250   0.9196   0.01159   0.00523  -0.0297   0.0063   1.0000
   6.500   0.9463   0.01197   0.00563  -0.0298   0.0056   1.0000
   6.750   0.9721   0.01261   0.00636  -0.0298   0.0049   1.0000
   7.000   0.9985   0.01296   0.00675  -0.0299   0.0045   1.0000
   7.250   1.0243   0.01345   0.00728  -0.0300   0.0041   1.0000
   7.500   1.0498   0.01397   0.00786  -0.0300   0.0037   1.0000
   7.750   1.0748   0.01453   0.00846  -0.0300   0.0035   1.0000
   8.000   1.0992   0.01517   0.00915  -0.0299   0.0032   1.0000
   8.250   1.1208   0.01632   0.01044  -0.0295   0.0030   1.0000
   8.500   1.1436   0.01710   0.01131  -0.0293   0.0029   1.0000
   8.750   1.1652   0.01805   0.01236  -0.0289   0.0027   1.0000
   9.000   1.1851   0.01917   0.01360  -0.0282   0.0026   1.0000
   9.250   1.2034   0.02047   0.01503  -0.0274   0.0024   1.0000
   9.500   1.2211   0.02176   0.01645  -0.0266   0.0023   1.0000
   9.750   1.2392   0.02291   0.01771  -0.0258   0.0022   1.0000
  10.000   1.2573   0.02394   0.01883  -0.0251   0.0021   1.0000
  10.250   1.2750   0.02492   0.01989  -0.0244   0.0020   1.0000
  10.500   1.2918   0.02589   0.02099  -0.0236   0.0019   1.0000
  10.750   1.3053   0.02721   0.02243  -0.0226   0.0018   1.0000
  11.000   1.3141   0.02892   0.02429  -0.0210   0.0018   1.0000
  11.250   1.3147   0.03109   0.02665  -0.0187   0.0017   1.0000
  11.500   1.3097   0.03426   0.03008  -0.0166   0.0017   1.0000
  11.750   1.2985   0.03862   0.03476  -0.0149   0.0016   1.0000
  12.000   1.2924   0.04238   0.03877  -0.0141   0.0016   1.0000
  12.250   1.2811   0.04698   0.04364  -0.0136   0.0016   1.0000
  12.500   1.2592   0.05336   0.05033  -0.0136   0.0016   1.0000
  12.750   1.2350   0.06026   0.05750  -0.0145   0.0016   1.0000
  13.000   1.2110   0.06734   0.06480  -0.0162   0.0016   1.0000
  13.250   1.1888   0.07438   0.07202  -0.0188   0.0016   1.0000
  13.500   1.1674   0.08152   0.07933  -0.0220   0.0016   1.0000
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