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NACA M19 AIRFOIL (m19-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA M19 AIRFOIL (m19-il)
Reynolds number: 1,000,000
Max Cl/Cd: 92.23 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m19-il-1000000-n5.txt
Download as CSV file: xf-m19-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M19 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3988   0.10241   0.09983   0.0133   0.6333   0.0028
  -7.750  -0.3929   0.09896   0.09638   0.0113   0.6278   0.0028
  -7.500  -0.3876   0.09553   0.09294   0.0090   0.6230   0.0028
  -7.250  -0.3781   0.09149   0.08889   0.0054   0.6185   0.0028
  -7.000  -0.3659   0.08748   0.08487   0.0015   0.6136   0.0030
  -6.750  -0.3508   0.08419   0.08154  -0.0020   0.6087   0.0031
  -6.500  -0.3342   0.08090   0.07823  -0.0054   0.6039   0.0032
  -6.250  -0.3161   0.07743   0.07472  -0.0090   0.5989   0.0034
  -6.000  -0.2964   0.07362   0.07086  -0.0130   0.5944   0.0035
  -5.750  -0.2750   0.06957   0.06676  -0.0170   0.5900   0.0038
  -5.500  -0.2513   0.06482   0.06194  -0.0216   0.5854   0.0043
  -5.250  -0.2247   0.05899   0.05601  -0.0269   0.5813   0.0046
  -5.000  -0.1975   0.05456   0.05150  -0.0309   0.5772   0.0049
  -4.750  -0.1714   0.05182   0.04867  -0.0334   0.5719   0.0053
  -4.500  -0.1432   0.04815   0.04489  -0.0363   0.5670   0.0058
  -4.250  -0.1120   0.04282   0.03939  -0.0399   0.5631   0.0070
  -4.000  -0.0841   0.04037   0.03686  -0.0416   0.5579   0.0077
  -3.750  -0.0561   0.03808   0.03444  -0.0430   0.5526   0.0085
  -3.500  -0.0233   0.03226   0.02835  -0.0453   0.5488   0.0108
  -3.250   0.0035   0.03152   0.02754  -0.0459   0.5431   0.0113
  -3.000   0.0309   0.03039   0.02631  -0.0465   0.5375   0.0122
  -2.750   0.0657   0.02307   0.01849  -0.0475   0.5343   0.0165
  -2.500   0.0925   0.02306   0.01845  -0.0478   0.5284   0.0168
  -2.000   0.1468   0.02190   0.01712  -0.0484   0.5174   0.0180
  -1.750   0.1745   0.02104   0.01615  -0.0487   0.5120   0.0190
  -1.500   0.2031   0.01950   0.01444  -0.0488   0.5071   0.0199
  -1.250   0.2320   0.01753   0.01224  -0.0488   0.5019   0.0204
  -1.000   0.2608   0.01544   0.00987  -0.0487   0.4963   0.0210
  -0.750   0.2894   0.01279   0.00680  -0.0483   0.4918   0.0218
  -0.500   0.3176   0.01212   0.00597  -0.0484   0.4866   0.0231
  -0.250   0.3458   0.01195   0.00571  -0.0485   0.4812   0.0239
   0.000   0.3740   0.01195   0.00566  -0.0486   0.4759   0.0244
   0.250   0.4016   0.01093   0.00448  -0.0488   0.4701   0.0272
   0.500   0.4296   0.01071   0.00420  -0.0490   0.4645   0.0283
   0.750   0.4577   0.01046   0.00391  -0.0491   0.4593   0.0294
   1.000   0.4858   0.01020   0.00359  -0.0493   0.4540   0.0303
   1.250   0.5138   0.00991   0.00324  -0.0493   0.4493   0.0305
   1.500   0.5417   0.00964   0.00293  -0.0494   0.4434   0.0306
   1.750   0.5696   0.00950   0.00273  -0.0496   0.4363   0.0315
   2.000   0.5974   0.00930   0.00250  -0.0496   0.4292   0.0315
   2.250   0.6251   0.00910   0.00226  -0.0497   0.4232   0.0307
   2.500   0.6529   0.00894   0.00208  -0.0498   0.4182   0.0299
   2.750   0.6807   0.00883   0.00195  -0.0499   0.4119   0.0292
   3.000   0.7086   0.00877   0.00187  -0.0500   0.4064   0.0286
   3.250   0.7365   0.00872   0.00183  -0.0501   0.4017   0.0281
   3.500   0.7643   0.00874   0.00182  -0.0503   0.3945   0.0277
   3.750   0.7919   0.00884   0.00186  -0.0505   0.3765   0.0273
   4.000   0.8193   0.00899   0.00193  -0.0507   0.3543   0.0271
   4.250   0.8467   0.00918   0.00204  -0.0509   0.3343   0.0269
   4.500   0.8727   0.00971   0.00230  -0.0511   0.2791   0.0268
   4.750   0.8923   0.01189   0.00351  -0.0512   0.0751   0.0268
   5.000   0.9174   0.01253   0.00396  -0.0512   0.0156   0.0270
   5.250   0.9443   0.01272   0.00418  -0.0513   0.0130   0.0280
   5.500   0.9709   0.01295   0.00447  -0.0514   0.0107   0.0338
   6.000   1.0287   0.01210   0.00545  -0.0531   0.0073   1.0000
   6.500   1.0788   0.01284   0.00624  -0.0527   0.0058   1.0000
   6.750   1.1025   0.01344   0.00690  -0.0524   0.0051   1.0000
   7.000   1.1272   0.01382   0.00730  -0.0523   0.0046   1.0000
   7.250   1.1511   0.01430   0.00785  -0.0520   0.0041   1.0000
   7.500   1.1745   0.01483   0.00842  -0.0517   0.0038   1.0000
   7.750   1.1975   0.01539   0.00901  -0.0514   0.0035   1.0000
   8.000   1.2174   0.01633   0.01004  -0.0508   0.0032   1.0000
   8.250   1.2371   0.01722   0.01102  -0.0502   0.0030   1.0000
   8.500   1.2556   0.01818   0.01207  -0.0494   0.0029   1.0000
   8.750   1.2712   0.01936   0.01336  -0.0483   0.0027   1.0000
   9.000   1.2835   0.02074   0.01488  -0.0469   0.0026   1.0000
   9.250   1.2942   0.02212   0.01636  -0.0454   0.0024   1.0000
   9.500   1.3042   0.02334   0.01766  -0.0439   0.0023   1.0000
   9.750   1.3105   0.02474   0.01914  -0.0424   0.0022   1.0000
  10.000   1.3199   0.02620   0.02067  -0.0418   0.0021   1.0000
  10.250   1.3284   0.02788   0.02243  -0.0413   0.0020   1.0000
  10.500   1.3367   0.02963   0.02425  -0.0408   0.0019   1.0000
  10.750   1.3419   0.03170   0.02641  -0.0401   0.0019   1.0000
  11.000   1.3453   0.03395   0.02875  -0.0393   0.0018   1.0000
  11.250   1.3447   0.03654   0.03146  -0.0377   0.0018   1.0000
  11.500   1.3439   0.03917   0.03425  -0.0352   0.0017   1.0000
  11.750   1.3495   0.04131   0.03652  -0.0330   0.0017   1.0000
  12.000   1.3622   0.04499   0.04051  -0.0270   0.0014   1.0000
  12.250   1.3651   0.04957   0.04541  -0.0244   0.0013   1.0000
  12.500   1.3591   0.05368   0.04975  -0.0231   0.0012   1.0000
  12.750   1.3496   0.05793   0.05422  -0.0223   0.0012   1.0000
  13.000   1.3380   0.06241   0.05889  -0.0219   0.0012   1.0000
  13.250   1.3246   0.06708   0.06375  -0.0219   0.0012   1.0000
  13.500   1.3094   0.07205   0.06889  -0.0224   0.0012   1.0000
  13.750   1.2931   0.07724   0.07425  -0.0233   0.0012   1.0000
  14.000   1.2755   0.08280   0.07996  -0.0247   0.0012   1.0000
  14.250   1.2570   0.08864   0.08596  -0.0265   0.0012   1.0000
  14.500   1.2388   0.09488   0.09235  -0.0289   0.0012   1.0000
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